An integrated aircraft model surface treatment hanger

Abstract

The utility model relates to a kind of hangers for integrated aircraft model surface treatment, including conducting frame body, the positioning net frame of several workpieces staggered array suspension limiting distribution point is hung and installed on the conducting frame body, detachably mounted with auxiliary limiting plate group on the top side of the positioning net frame, and detachably inserted with the clamping mechanism that workpiece can be hung below the positioning net frame on the bottom side of the positioning net frame, wherein, the side edge of the frame of the positioning net frame is connected with the hanging footboard limiting its assembly position on the conducting frame body, several insertion sleeves connected with it by grid frame rod are provided in the frame cavity of the frame, and adjacent two insertion sleeves are also connected by the grid frame rod. The utility model can improve the plating effect and quality of aircraft model blank and ensure the integrity of plating film layer.

Description

Technical Field

[0001] This utility model relates to the field of fixtures for aircraft model processing, and in particular to an integrated fixture for surface treatment of aircraft models. Background Technology

[0002] Aircraft models are generally divided into two types: dynamic and static. Static models are used for collection, display, and wind tunnel testing, and are scaled-down versions of aircraft. Currently, one-piece metal aircraft models are produced using injection molds. To reduce defects such as voids and pinholes in the molded model, a sprue is usually placed in the area of ​​the mold corresponding to the tail section of the aircraft model to ensure the saturation and fullness of the casting. Therefore, after casting and solidification, the tail section of the aircraft model usually has a casting allowance rod that matches the sprue runner and is integrally connected to the aircraft model blank.

[0003] For example, patent document CN202110344246.0 discloses an aircraft model casting mold, including a mold body. The top of the mold body is provided with a casting port and an exhaust port. The mold body includes a detachably connected left half mold and a right half mold. The left half mold is provided with a first cavity, a first continuous curved groove and a first exhaust groove. The right half mold is provided with a second cavity, a second continuous curved groove and a second exhaust groove. The first cavity and the second cavity are connected to form an integral cavity of the aircraft model. The first continuous curved groove and the second continuous curved groove are connected to form a continuous curved path that communicates with the casting port. The continuous curved path is a gentle curve, and the bottom of the continuous curved path is connected to the bottom of the integral cavity. The first exhaust groove and the second exhaust groove are connected to form an exhaust channel that communicates with the exhaust port. The left side of the left half mold and the right side of the right half mold are respectively provided with grooves for reducing the weight of the device.

[0004] One-piece metal aircraft models typically have a monolithic surface structure. To improve the surface quality and aesthetics of these models, surface treatment is usually required to enhance their surface quality and performance. Existing conventional surface treatment operations include cleaning, polishing, and surface film processing. Among these, to improve the quality, performance, and adhesion of the surface film, electroplating is usually performed on the aircraft model blank before coating to improve its surface properties.

[0005] Currently, existing electroplating operations typically involve randomly stacking aircraft model blanks in electroplating baskets, then using a cleaning line clamping and transfer system to periodically and orderly move the baskets into and out of electroplating tanks or other liquid baths to achieve surface electroplating. However, randomly stacked aircraft model blanks often have dead zones where they come into contact with or block each other, preventing the film molecules from effectively depositing on the workpiece surface during electroplating, resulting in poor quality electroplated layers. Furthermore, the stacked aircraft model blanks may experience relative movement during processing and transportation, leading to surface collisions and friction, which can damage the electroplated layer and affect its integrity and overall performance. Utility Model Content

[0006] The purpose of this utility model is to provide an integrated aircraft model surface treatment fixture that can improve the electroplating effect and quality of aircraft model blanks and ensure the integrity of the electroplating film. This solves the problems of existing aircraft model blanks being stacked disorderly in electroplating baskets, resulting in dead corners where the blanks contact or block each other, making it impossible to electroplat a complete and uniform electroplating film, and the collisions and friction between the disorderly stacked blanks affecting the integrity and quality of the electroplating layer.

[0007] The technical solution adopted by this utility model is as follows: an integrated hanger for surface treatment of aircraft models, including a conductive frame, on which a positioning grid frame capable of defining the distribution points of a plurality of workpieces in a staggered array suspension is horizontally hung. An auxiliary limiting plate group is detachably installed on the top side of the positioning grid frame, and a clamping mechanism capable of suspending the workpieces below the positioning grid frame is detachably inserted on the bottom side of the positioning grid frame. The side of the frame of the positioning grid frame is connected to a hanging foot plate that defines its assembly position on the conductive frame. A plurality of insert sleeves connected to the frame cavity of the frame are provided through a grid frame rod, and two adjacent insert sleeves are also connected through the grid frame rod.

[0008] According to a preferred embodiment, the limiting pin of the auxiliary limiting plate assembly is detachably inserted into the upper axial end of the insert sleeve, and the insert rod of the clamping mechanism is detachably inserted into the lower axial end of the insert sleeve.

[0009] According to a preferred embodiment, two vertical sliding grooves are aligned and formed on the inner wall of the axial lower section of the insert sleeve, and the top of the vertical sliding grooves are connected to the hanging sliding groove through a transverse sliding groove.

[0010] According to a preferred embodiment, the lower axial end of the insert rod of the clamping mechanism is connected to a threaded rod, and an internally threaded sleeve is threaded onto the threaded rod; the lower axial end of the threaded rod is connected to a clamping head whose working posture is defined by the internally threaded sleeve.

[0011] According to a preferred embodiment, two limiting protrusions are provided on the top side of the insert hanging rod, which can slide in the vertical sliding groove, the horizontal sliding groove and the hanging groove.

[0012] According to a preferred embodiment, the clamping head includes a threaded column head that is connected to the threaded rod, a connecting cylinder connected to the axial lower end of the threaded column head, and arc-shaped clamping pieces that are integrally connected to the connecting cylinder and arranged circumferentially. The outer wall surface of the arc-shaped clamping pieces is also covered with sloping arc plates.

[0013] According to a preferred embodiment, the hanging plates of the conductive frame are aligned and connected to both sides of the annular suspension plate frame, and two inverted U-shaped hanging rods are also aligned and arranged on the top side of the annular suspension plate frame; the bottom side of the annular suspension plate frame is provided with a hollowed-out enclosure.

[0014] According to a preferred embodiment, a grid plate is provided in the connecting plate frame of the auxiliary limiting plate assembly, and a plurality of limiting pins corresponding to the insert sleeve are arranged in a staggered array on the bottom surface of the grid plate.

[0015] According to a preferred embodiment, a groove is provided on the plate body of the mounting plate for inserting the mounting foot plate.

[0016] According to a preferred embodiment, a stabilizing perforated plate is also connected to the bottom side of the perforated enclosure.

[0017] The beneficial effects of this utility model are:

[0018] The clamping mechanism provided in this application can clamp aircraft model blanks with casting allowance rods, thereby hanging several aircraft model blanks on the positioning frame with intervals and without contact through a plug-in connection. This ensures that several aircraft model blanks can be effectively immersed in the electrolytic tank along with the conductive frame to complete a full and effective electroplating process. Furthermore, the mutually separated hanging method can effectively avoid contact, collision, or friction between the aircraft model blanks, ensuring the comprehensiveness and uniformity of the film deposition coverage. It can also prevent damage to the electroplated film layer during the transfer process, effectively improving the quality and yield of the electroplating process, and enhancing the surface treatment effect and surface performance of the aircraft model blanks as workpieces. Attached Figure Description

[0019] Figure 1This is a schematic diagram of a preferred integrated aircraft model surface treatment fixture proposed in this utility model;

[0020] Figure 2 This is a plan view of a preferred integrated aircraft model surface treatment fixture positioning frame proposed in this utility model.

[0021] Figure 3 This is an axial cross-sectional schematic diagram of a preferred clamping mechanism for an integrated aircraft model surface treatment hanger proposed in this utility model.

[0022] Figure 4 This is a schematic diagram of the unfolded plan view of the insert sleeve of a preferred integrated aircraft model surface treatment fixture proposed in this utility model.

[0023] Figure 5 This is a partial axial planar schematic diagram of the clamping head of a preferred integrated aircraft model surface treatment hanger proposed in this utility model.

[0024] Figure 6 This is a schematic diagram of the structure of a preferred integrated aircraft model surface treatment fixture proposed in this utility model when suspended in an electroplating tank.

[0025] List of reference numerals

[0026] 1: Conductive frame; 2: Positioning grid frame; 3: Auxiliary limiting plate assembly; 4: Clamping mechanism; 11: Hanging plate; 12: Circular suspension plate frame; 13: Inverted U-shaped hanging rod; 14: Hollowed-out enclosure; 15: Stabilizing hollowed-out plate; 111: Groove; 21: Frame; 22: Grid frame rod; 23: Insert sleeve; 24: Hanging foot plate; 231: Vertical slide groove; 232: Horizontal slide groove; 233: Hanging slide groove; 31: Limiting insert; 32: Connecting plate frame; 33: Grid plate; 41: Insert hanging rod; 42: Threaded rod; 43: Internal threaded sleeve; 44: Clamping head; 411: Limiting protrusion; 441: Threaded column head; 442: Connecting middle cylinder; 443: Arc-shaped clamp; 444: Sloping arc plate. Detailed Implementation

[0027] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the present utility model will be briefly introduced below in conjunction with the accompanying drawings and descriptions of the embodiments or the prior art. Obviously, the following description of the structure of the drawings is only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0028] The technical solutions provided by this utility model will be described in detail below with reference to the accompanying drawings and through embodiments. It should be noted that the description of these embodiments is for the purpose of helping to understand this utility model, but does not constitute a limitation thereof. In some examples, because some implementation methods belong to existing or conventional technology, they are not described or are not described in detail. The serial numbers assigned to components in this document, such as "first," "second," etc., are only used to distinguish the described objects and do not have any sequential or technical meaning.

[0029] The following is a detailed explanation with reference to the accompanying drawings.

[0030] Example 1

[0031] This application provides an integrated mounting bracket for surface treatment of an aircraft model, which includes a conductive frame 1, a positioning mesh frame 2, an auxiliary limiting plate group 3, and a clamping mechanism 4.

[0032] according to Figure 1-6In one specific embodiment, the conductive frame 1 is detachably attached to a lifting gripper used for material handling and transfer on an electroplating line. The conductive frame 1, through direct contact with the lifting gripper, connects the entire fixture structure to the negative terminal of the power supply, allowing several aircraft model blanks on the fixture to act as cathodes, attracting electroplating molecules to adhere to their surfaces during the electroplating process. A positioning grid 2, capable of defining the distribution points for the staggered suspension of several workpieces, is horizontally mounted on the conductive frame 1. An auxiliary limiting plate assembly 3 is detachably installed on the top side of the positioning grid 2. A clamping mechanism 4 is detachably inserted into the bottom side of the positioning grid 2, capable of adapting and clamping the casting allowance rods integrally connected to the workpiece blank formed during casting, thereby suspending the workpiece below the positioning grid 2. The positioning grid 2 includes a frame 21, a grid frame rod 22, an insert sleeve 23, and a mounting foot plate 24. The side of the frame 21 of the positioning frame 2 is connected to an inverted L-shaped mounting foot plate 24 that defines its assembly position on the conductive frame 1. The mounting foot plate 24 defines the assembly position of the frame 21 by inserting a movable clip into the mounting plate 11 of the conductive frame 1. Several insert sleeves 23 are arranged in a staggered array in the frame cavity of the frame 21 and connected to it by a grid frame rod 22. Two adjacent insert sleeves 23 are also connected by a grid frame rod 22, so that the insert sleeve 23 defines its relative position with the frame 21 and the adjacent insert sleeve 23 by multiple grid frame rods 22 connected to its outer cylinder wall. A limiting post 31 of the auxiliary limiting plate group 3 is detachably inserted into the upper axial end of the insert sleeve 23. An insert hanging rod 41 of the clamping mechanism 4 is also detachably inserted into the lower axial end of the insert sleeve 23. The clamping mechanism 4 provided in this application can clamp aircraft model blanks with casting allowance rods, thereby hanging several aircraft model blanks on the positioning frame 2 with intervals and without contact through a plug-in connection. This ensures that the aircraft model blanks can be effectively immersed in the electrolytic tank along with the conductive frame 1 to complete a full and effective electroplating process. The mutually separated hanging method can effectively avoid contact, collision, or friction between the aircraft model blanks, ensuring the comprehensiveness and uniformity of the film deposition coverage, and also preventing damage to the electroplated film layer during the transfer process. This effectively improves the quality and yield of the electroplating process, and enhances the surface treatment effect and surface performance of the aircraft model blanks as workpieces. The clamping mechanism 4 provided in this application can adaptably and stably clamp casting allowance rods of different thicknesses, ensuring stable clamping of aircraft model blanks with casting deviations.

[0033] Preferably, the mounting plates 11 of the conductive frame 1 are aligned and connected to both sides of the annular suspension frame 12. Preferably, two inverted U-shaped hanging rods 13 are also aligned and arranged on the top side of the annular suspension frame 12. Preferably, a perforated enclosure 14 with support and structural rigidity is arranged circumferentially on the bottom side of the annular suspension frame 12. Preferably, a stabilizing perforated plate 15 is also connected to the bottom side of the perforated enclosure 14, which can catch and intercept falling workpieces and improve the structural stability of the perforated enclosure 14. Preferably, the mounting plates 11, inverted U-shaped hanging rods 13 and perforated enclosure 14 are all fixed to the annular suspension frame 12 by welding. Preferably, a groove 111 for inserting the mounting feet 24 is opened on the plate body of the mounting plate 11. The conductive frame 1 provided in this application has a conductive frame-like structure that can effectively prevent external equipment from impacting the aircraft model blank, so as to ensure the integrity of the surface film layer of the aircraft model.

[0034] Preferably, the inverted U-shaped hanging rod 13, the annular suspension plate frame 12, and the hanging plate 11 of the conductive frame 1 are rigidly connected by welding or other means to ensure conductivity, so that the conductive frame 1 can be connected to the negative terminal of the power supply by hanging on the gripper.

[0035] Preferably, during the electroplating operation, the height of the conductive frame 1 and the pre-set lifting values ​​of the lifting claws are predetermined. This ensures that when the aircraft model blank is immersed in the electrolytic tank, the depth of the electrolyte in the tank is also pre-designed. In other words, the liquid level in the tank completely submerges the aircraft model blank, but does not reach the height of the clamping mechanism 4, thus placing the clamping mechanism 4 above the liquid level and reducing the possibility of corrosion or electroplating of the clamping mechanism 4. Preferably, the annular suspension plate frame 12 and the perforated enclosure 14, and the perforated enclosure 14 and the stabilizing perforated plate 15 are connected to each other by binding, welding, or other methods to ensure structural stability. Specifically, the stabilizing perforated plate 15 for the structural stability of the perforated enclosure 14 is made of rubber-coated stainless steel, which does not react with the electrolyte, allowing it to enter and exit the electrolytic tank intact and without contamination.

[0036] Preferably, two vertical grooves 231 are formed on the inner wall of the lower axial section of the insert sleeve 23. More preferably, the top of the vertical groove 231 is connected to the hanging groove 233 through a transverse groove 232, thereby forming a continuous asymmetrical U-shaped hanging groove cavity that can be adapted to the limiting protrusion 411 on the insert hanging rod 41 to limit the insertion and hanging state of the insert hanging rod 41. Preferably, the length of the limiting pin 31 inserted at the top of the insert sleeve 23 is greater than the difference between the length of the insert sleeve 23 and the vertical groove 231, so that when the insert hanging rod 41 is hooked in the hanging groove 233, the limiting pin 31 inserted from top to bottom into the insert sleeve 23 can limit the upward falling movement of the insert hanging rod 41, thereby limiting the hanging posture and relative position of the insert hanging rod 41. Preferably, the insert rod 41 can be inserted from the lower end of the insert sleeve 23, and the limiting protrusion 411 slides into the vertical groove 231 simultaneously. When the limiting protrusion 411 moves to the top of the vertical groove 231 with the insert rod 41, the limiting protrusion 411 moves in an arc along the horizontal groove 232 and enters the hanging groove 233 by rotating the insert rod 41. Then, under its own weight without external force, the insert rod 41 pulls the limiting protrusion 411 down so that the limiting protrusion 411 is stuck in the hanging groove 233, thereby limiting the hanging posture and position of the insert rod 41 in the insert sleeve 23. In the above assembly posture, the limiting pin 31 is inserted into the cavity of the insertion sleeve 23 from the top end, so that the limiting pin 31 can resist the upward movement of the insertion rod 41, thereby limiting the relative position of the limiting protrusion 411 in the mounting slide 233, thereby ensuring the stability of the insertion rod 41 in the insertion sleeve 23, so as to realize that the aircraft model blank is stably suspended by the clamping mechanism 4 below the positioning frame 2.

[0037] Preferably, a grid plate 33 is provided within the connecting frame 32 of the auxiliary limiting plate assembly 3. Preferably, a plurality of limiting posts 31 corresponding to the insert sleeve 23 are arranged in a staggered array on the bottom surface of the grid plate 33. Preferably, a magnetic attractant is embedded in the bottom surface of the connecting frame 32, so that it can be effectively magnetically connected to the frame 21. Preferably, the limiting posts 31, the grid plate 33, and the connecting frame 32 are fixedly connected by welding or other means. The auxiliary limiting plate assembly 3 provided in this application ensures the stability of the downward insertion by its own weight, and at the same time ensures the stability of the insertion connection of the clamping mechanism 4, so that the entire assembly structure has high limiting assembly stability. The auxiliary limiting plate assembly 3 mainly uses its own weight to press down to achieve pressure limiting, which ensures the stability of the assembly connection while facilitating disassembly, so that it can be quickly disassembled and removed after tilting.

[0038] Preferably, the lower axial end of the insert rod 41 of the clamping mechanism 4 is connected to a threaded rod 42. More preferably, an internally threaded sleeve 43 is threaded onto the threaded rod 42. Preferably, the lower axial end of the threaded rod 42 is connected to a clamping head 44, which can be fitted onto the cast allowance rod body integrally connected to the workpiece blank and whose working posture is limited by the internally threaded sleeve 43, which can adjustably undergo axial translation. Preferably, two limiting protrusions 411 are aligned on the top side of the insert rod 41 by welding or integral forming, which can slide in the vertical slide groove 231, the horizontal slide groove 232, and the hanging slide groove 233. Preferably, the lower axial end of the threaded rod 42 is provided with an internally threaded slot that matches the threaded post head 441, facilitating quick replacement of the clamping head 44. During clamping, the operator first manually inserts the casting allowance rod from the tail of the aircraft model blank into the clamping head 44. Then, by screwing the internal threaded sleeve 43, the internal threaded sleeve 43 is moved axially, causing the clamping head 44 to change shape and stably clamp the casting allowance rod, thus achieving a detachable connection between the clamping mechanism 4 and the aircraft model blank. Then, the operator inserts the insertion rod 41 into the insertion sleeve 23 and manually rotates it to a certain extent, causing the limiting protrusion 411 to move into the mounting groove 233, thereby achieving effective engagement between the insertion rod 41 and the insertion sleeve 23, and thus suspending the aircraft model blank on the positioning frame 2.

[0039] Preferably, the side of the internally threaded sleeve 43 is also threaded with a locking screw to help limit its position on the threaded rod 42. When the internally threaded sleeve 43 effectively presses against the constraint clamping head 44 to effectively clamp the casting allowance rod, the operator can adjust the locking screw to improve the stability of the internally threaded sleeve 43 and ensure the stability of the clamping.

[0040] Preferably, the clamping head 44 includes a threaded stud 441 that engages with the threaded rod 42, a connecting cylinder 442 connected to the axially lower end of the threaded stud 441, and arc-shaped clamping pieces 443 integrally connected to the connecting cylinder 442 and arranged circumferentially. Preferably, the outer wall surface of the arc-shaped clamping pieces 443 is also covered with a ramped arc plate 444, so that the downward movement of the inner threaded sleeve 43 can reduce the distance between the arc-shaped clamping pieces 443 and the central axis by forcing the ramped arc plate 444 to move radially inward, thereby allowing multiple arc-shaped clamping pieces 443 to cooperate in clamping the centrally inserted casting allowance rod. Preferably, the threaded stud 441 and the connecting cylinder 442, and the arc-shaped clamping pieces 443 and the ramped arc plate 444 are connected by welding or integral machining. Specifically, the arc-shaped clamping pieces 443 are formed by axially cutting multiple circumferentially spaced notches into the tube body constituting the connecting cylinder 442, and the two are integral. Specifically, the arc-shaped clamp 443 provided in this application is prone to problems such as connection cracks at the connection point with the connecting cylinder 442 after repeated bending and clamping deformation. Therefore, it can be replaced periodically as needed. The quick-release structure provided in this application can improve the efficiency of disassembly and replacement, and reduce the replacement cost of parts. This application uses a high-toughness stainless steel tube to make the arc-shaped clamp 443 and the connecting cylinder 442, which to a certain extent improves the service life of the structural components and ensures their conductivity.

[0041] For surface connections between components not explicitly specified in this application, conventional bolt connections, snap-fit ​​connections, or fixed connections such as welding can be used. As these are conventional connection methods, this application will not elaborate further on this part. Specifically, the connecting ends of the assembled components all form flange structures, and the two flange structures are connected by bolts, gaskets, or other structures.

[0042] This utility model is not limited to the above-described optional embodiments. Anyone can derive other various forms of products under the guidance of this utility model. However, regardless of any changes in shape or structure, any technical solution falling within the scope of the claims of this utility model is within the protection scope of this utility model. Those skilled in the art should understand that this utility model specification and its drawings are illustrative and do not constitute a limitation on the claims. The protection scope of this utility model is defined by the claims and their equivalents. Throughout the text, features introduced by "preferred" are merely optional and should not be construed as mandatory. Therefore, the applicant reserves the right to abandon or delete relevant preferred features at any time.

Claims

1. A mounting bracket for surface treatment of an integrated aircraft model, comprising a conductive frame (1), characterized in that, A positioning grid frame (2) capable of defining the distribution points of a plurality of workpieces in a staggered array suspension is horizontally mounted on the conductive frame (1). An auxiliary limiting plate assembly (3) is detachably installed on the top side of the positioning grid frame (2), and a clamping mechanism (4) capable of suspending the workpieces below the positioning grid frame (2) is detachably inserted into the bottom side of the positioning grid frame (2). The side of the frame (21) of the positioning frame (2) is connected to a mounting foot plate (24) that defines its assembly position on the conductive frame (1). A plurality of insert sleeves (23) are provided in the frame cavity of the frame (21) and connected to it by a grid frame rod (22). Two adjacent insert sleeves (23) are also connected by the grid frame rod (22).

2. The integrated aircraft model surface treatment fixture as described in claim 1, characterized in that, The limiting pin (31) of the auxiliary limiting plate group (3) is detachably inserted into the upper axial end of the insert sleeve (23), and the insert hanging rod (41) of the clamping mechanism (4) is detachably inserted into the lower axial end of the insert sleeve (23).

3. The integrated aircraft model surface treatment fixture as described in claim 2, characterized in that, Two vertical grooves (231) are aligned on the inner wall of the lower axial section of the insert sleeve (23), and the top of the vertical grooves (231) are connected to the hanging grooves (233) through the transverse grooves (232).

4. The integrated aircraft model surface treatment fixture as described in claim 3, characterized in that, The lower axial end of the insertion rod (41) of the clamping mechanism (4) is connected to a threaded rod (42), and an internal threaded sleeve (43) is threaded onto the threaded rod (42). The lower axial end of the threaded rod (42) is connected to a clamping head (44) whose working posture is defined by the internal threaded sleeve (43).

5. The integrated aircraft model surface treatment fixture as described in claim 4, characterized in that, Two limiting protrusions (411) are provided on the top side of the insert hanging rod (41) so that they can slide in the vertical sliding groove (231), the horizontal sliding groove (232) and the hanging sliding groove (233).

6. The integrated aircraft model surface treatment fixture as described in claim 5, characterized in that, The clamping head (44) includes a threaded stud (441) that is connected to the threaded rod (42), a connecting cylinder (442) connected to the lower axial end of the threaded stud (441), and arc-shaped clamping pieces (443) that are integrally connected to the connecting cylinder (442) and arranged at circumferential intervals. The outer wall surface of the arc-shaped clip (443) is also covered with a sloping arc-shaped clip (444).

7. The integrated aircraft model surface treatment fixture as described in claim 6, characterized in that, The hanging plate (11) of the conductive frame (1) is aligned and connected to both sides of the annular suspension plate frame (12), and two inverted U-shaped hanging rods (13) are also aligned and arranged on the top side of the annular suspension plate frame (12). The bottom side of the annular suspension plate frame (12) is provided with a hollowed-out enclosure (14).

8. The integrated aircraft model surface treatment fixture as described in claim 7, characterized in that, A grid plate (33) is provided in the connecting plate frame (32) of the auxiliary limiting plate group (3), and a number of limiting pins (31) corresponding to the insert sleeve (23) are arranged in a staggered array on the bottom surface of the grid plate (33).

9. The integrated aircraft model surface treatment fixture as described in claim 8, characterized in that, The mounting plate (11) has a groove (111) for inserting the mounting foot plate (24).

10. The integrated aircraft model surface treatment fixture as described in claim 9, characterized in that, A stabilizing perforated plate (15) is also connected to the bottom side of the perforated enclosure (14).

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