Whole-fuselage static test transfer device

Abstract

The utility model discloses a full-fuselage static test transfer device which is characterized in that two sets of wing brackets are symmetrically arranged on two sides of a main body bracket to form a bracket assembly; the AGV stretches across the bottoms of the main body bracket and the wing brackets on the two sides in the spanwise direction; the transfer bracket is rapidly clamped and embedded in the upper portion of the AGV through a pressing structure arranged on the side edge in the spanwise direction of the transfer bracket, and the bracket assembly is rapidly limited through a limiting baffle arranged on the transfer bracket, so that the transfer bracket installed on the AGV in a clamped and embedded mode is used for carrying out transfer supporting on the bracket assembly; the bracket assembly and the aircraft mounted on the bracket assembly are precisely displaced through the AGV; and wheel sets are arranged at the bottoms of the main body bracket and the wing brackets and are moved under the dragging of the tractor. According to the technical scheme provided by the utility model, the problem that an airplane is mounted on a transfer device during the mounting process of a test facility in the existing full-airplane static test, and the transfer device can only be separated from a gap of a bearing upright post after being partitioned after the mounting is completed is solved.

Description

TECHNICAL FIELD

[0001] The utility model relates to but not limited to the technical field of aircraft manufacturing, especially a full fuselage static test transfer device. BACKGROUND

[0002] Full fuselage static test needs to pass a set of complex loading device and a complete system, to simulate a series of complex loads such as air force and engine thrust that aircraft receives in the air; the load is truly applied on the aircraft, to measure whether the real aircraft structure meets the strength requirement in the whole flight process. An aircraft wants to soar in the sky, must pass the test of aviation industry strength, can obtain the pass certificate. And full fuselage static test is one of the most important tests.

[0003] Because the aircraft manufacturing workshop and the test site are two different units, the two sites have a certain geographical distance. The aircraft span width is far more than the heading width, and the heading land transportation cost is too high, when carrying out full fuselage static test, the landing gear is a finished product, the price is high and the cycle is long, consider using a false piece to assemble when carrying out full fuselage static test, to save cost and improve production progress. Therefore, when carrying out full fuselage static test, the aircraft needs a special transfer device to accurately transfer the aircraft from the manufacturing unit to the designated position of the test site of the test unit. Consider using the existing AGV car to carry out road transportation work, and transfer to the test site, and then carry out test facility preparation and installation work, including the installation of test bearing column, during which the aircraft will be on the transfer device all the time, until all the preparation work is completed, the aircraft is lifted, and the transfer device is no longer needed. At this time, the test bearing column is installed, and the transfer device can be removed from the gap of the bearing column in blocks. UTILITY MODEL CONTENTS

[0004] The utility model discloses a full fuselage static test transfer device to solve the problem that the aircraft is installed on the transfer device during the installation of the test facility of the existing full fuselage static test, and after the installation of the test bearing column, the transfer device can only be removed from the gap of the bearing column in blocks.

[0005] The utility model discloses a full fuselage static test transfer device, including: two sets of wing bracket 1, a set of main body bracket 2, a set of adapter bracket 3, and AGV car 4 and tractor 5.

[0006] The two sets of wing brackets 1 are symmetrically arranged on the two sides of the main bracket 2, and the main bracket 2 and the two sets of wing brackets 1 are arranged according to the shape of the aircraft, and are connected by a detachable connection to form a bracket assembly; the plumb line of the bracket assembly is collinear with the plumb line of the aircraft; the AGV vehicle 4 is arranged along the span direction and crosses the bottom of the main bracket 2 and the two sets of wing brackets 1, and the plumb line of the bracket assembly is located on the central axis of the AGV vehicle 4;

[0007] The adapter bracket 3 is quickly clamped on the upper part of the AGV vehicle 4 through the pressing structure arranged on the span direction side of the adapter bracket 3, and the adapter bracket 3 is quickly limited by the limiting baffle 35 arranged on the adapter bracket 3, so that the adapter bracket 3 clamped on the AGV vehicle 4 can adapt and support the bracket assembly, and the AGV vehicle 4 can accurately displace the bracket assembly and the aircraft installed on the bracket assembly.

[0008] The bottom of the main bracket 2 and the two sets of wing brackets 1 are provided with a wheel set for displacement under the dragging of the tractor 5.

[0009] Optionally, in the full-fuselage static test transfer device described above,

[0010] The main bracket 2 is arranged as a square frame structure as a whole, and is used to carry the aircraft fuselage. Fixed brackets 21 are arranged on the main load-bearing frames near the nose and the tail of the fuselage, respectively. One of the fixed brackets 21 is symmetrically provided with a group of vertically downward removable ball socket structures 22 along the span direction, which are used to cooperate with the two process ball heads below the fuselage along the span direction to position and connect the aircraft fuselage.

[0011] The main bracket 2 is provided with a fuselage adjustable bracket 23 on the main load-bearing frame at the nose position, which is used to adjust the height of the fuselage adjustable bracket 23 to make all the bracket structures in the bracket assembly support the aircraft body structure.

[0012] Optionally, in the full-fuselage static test transfer device described above, the main bracket 2 is provided with four rows of wheel sets along the heading direction. The two wheel sets in the middle are load-bearing wheel sets 24 for displacement, and the front and rear wheel sets along the heading direction are anti-rollover wheel sets 25, and the anti-rollover wheel sets 25 are higher than the load-bearing wheel sets 24 to prevent rollover during the transfer process.

[0013] Optionally, in the full-fuselage static test transfer device described above,

[0014] The side frame width of each wing bracket 1 is the same as the length of the main bracket 2 along the heading, and is used to form a quick-release connection structure with the main bracket 2 through the side frame; each wing bracket 1 is provided with two groups of wing adjustable brackets 11 at the wing main load-bearing frame close to the fuselage side, for supporting the wing structure of the corresponding side by adjusting each group of wing adjustable brackets 11, and the wing adjustable bracket 11 located at the outer rear side is provided with a camouflage support 12 for supporting the wing in cooperation with the wing adjustable bracket 11; the bottom of each wing bracket 1 is provided with four groups of load-bearing wheel sets 24.

[0015] Optionally, in the full-fuselage static test transfer device described above, the adapter bracket is integrally provided as a truss structure, comprising: three groups of adapter sub-brackets, one main adapter bracket 32 located in the middle, and two groups of wing adapter brackets 31 located on both sides of the main adapter bracket 32;

[0016] Among them, the three groups of adapter sub-brackets and the AGV car 4 are quickly fixed through the wedge-shaped compression structure 33 and the cooperatively used wedge-shaped block 34;

[0017] The three groups of adapter sub-brackets and the bracket assembly are clamped and fixed through the limiting baffle 35 installed on each group of adapter sub-brackets.

[0018] Optionally, in the full-fuselage static test transfer device described above, the main adapter bracket 32 and the two groups of wing adapter brackets 31 are provided with wedge-shaped compression structures 33 along the vehicle body of the AGV car 4 and are arranged on both sides in the span direction, and the wedge-shaped block 34 is pressed into the wedge-shaped compression structure 33 to quickly fix the adapter bracket 3 and the AGV car 4;

[0019] The main adapter bracket 32 and the two groups of wing adapter brackets 31 are provided with limiting baffles 35 with handles around the periphery, and the limiting baffles 35 are provided with three connecting holes arranged in an equilateral triangle at the lower part. Before the main bracket 2 and the two side wing brackets 1 are installed, the middle connecting hole 36 of the limiting baffle 35 is connected with the truss structure of the adapter bracket 3, and the limiting baffle 35 is rotated to the lowest position. After the main bracket 2 and the two side wing brackets 1 are erected on the wing adapter bracket 31 and the main adapter bracket 32, the limiting baffle 35 is rotated to the highest position around the middle connecting hole 36, and then the lower two connecting holes 37 are fixedly connected with the truss, so that the main bracket 2 and the two side wing brackets 1 are clamped and fixed on the adapter bracket 3.

[0020] The utility model discloses beneficial effect: the utility model embodiment provides a full fuselage static test transfer device, solved the aircraft of no landing gear, span transportation from manufacturing unit accurate transportation to test unit test specified position, test facility installation cooperation etc. The utility model provides full fuselage static test transfer device, utilize the wedge compression structure of adapter bracket 3, can realize the quick fixing between ordinary AGV car 4 and bracket assembly;The lowest position and the highest position of limiting baffle 35 of adapter bracket 3 are switched, and the quick card embedding between bracket assembly and adapter bracket 3 can be realized;The space requirement of test site can be cooperated by the wing bracket 1 of combinable split and main bracket 2;Through the combination of fixed bracket 21 and fuselage adjustable bracket 23, the ball socket structure 22 of vertical downward removal, the accurate positioning and reliable positioning of the aircraft on main bracket 1 can be realized;The transportation and rollover problem in the transportation process is guaranteed by the difference of the height of the wheel group in main bracket 1. The utility model embodiment provides full fuselage static test transfer device's simple structure, can utilize the existing transfer car and save the cost greatly, and installation and removal are simple, and can be repeatedly used, guarantee the transportation safety of product;In addition, the transfer device can be directly popularized to all whole machine transportation technical field. BRIEF DESCRIPTION OF DRAWINGS

[0021] The drawings are used to provide further understanding of the technical scheme of the utility model, and constitute a part of the specification, and are used together with the embodiments of the application to explain the technical scheme of the utility model, and do not constitute the limitation to the technical scheme of the utility model.

[0022] Figure 1 The whole structure schematic diagram of the full fuselage static test transfer device provided for the utility model embodiment is shown in the figure;

[0023] Figure 2 For Figure 1 The structure schematic diagram of the main bracket in the full fuselage static test transfer device provided for the embodiment shown in the figure is shown in the figure;

[0024] Figure 3 For Figure 2 The structure schematic diagram of the ball socket structure of vertical downward removal in the main bracket provided for the embodiment shown in the figure is shown in the figure;

[0025] Figure 4 For Figure 1 The structure schematic diagram of the main bracket in the full fuselage static test transfer device provided for the embodiment shown in the figure is shown in the figure;

[0026] Figure 5 For Figure 1 The structure schematic diagram of the adapter bracket in the full fuselage static test transfer device provided for the embodiment shown in the figure is shown in the figure.

[0027] Mark explanation:

[0028] 1. Wing bracket; 11. Adjustable wing bracket; 12. Camouflage support; 2. Main body bracket; 21. Fixed bracket; 22. Ball socket structure; 23. Adjustable fuselage bracket; 24. Load-bearing wheel assembly; 25. Anti-rollover wheel assembly; 3. Adapter bracket; 31. Wing adapter bracket; 32. Main body adapter bracket; 33. Wedge clamping structure; 34. Wedge block; 35. Limiting baffle; 36. Middle connecting hole; 37. Connecting hole; 4. AGV vehicle; 5. Tractor vehicle. Detailed Implementation

[0029] To make the objectives, technical solutions, and advantages of this utility model clearer, the embodiments of this utility model will be described in detail below with reference to the accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

[0030] As explained in the background section, static testing of the entire aircraft is a necessary test for its flight. In existing static testing procedures, during the transfer of the aircraft and the installation of the test facilities, the aircraft remains on the transfer device until all test equipment is installed and the aircraft is lifted to remove it from the transfer device. However, at this point, the test support columns are installed, and the transfer device can only be dismantled by dividing it into sections and removing it through the gaps between the support columns.

[0031] To address the aforementioned problems, this utility model provides a full-fuselage static test transport device.

[0032] The present invention provides the following specific embodiments, which can be combined with each other. For the same or similar concepts or processes, they will not be described again in some embodiments.

[0033] Figure 1 A schematic diagram of the overall structure of a static test transfer device for the entire fuselage provided in this embodiment of the utility model; Figure 2 for Figure 1 The illustrated embodiment provides a schematic diagram of the main support structure in the static test transfer device for the entire fuselage. The static test transfer device for the entire fuselage provided in this embodiment includes: two sets of wing supports 1, one set of main support 2, one set of transfer support 3, one AGV vehicle 4, and one tractor vehicle 5.

[0034] like Figure 1As shown, in this embodiment of the present invention, two sets of wing brackets 1 are symmetrically arranged on both sides of the main body bracket 2. According to the shape of the aircraft, the wing brackets 1 and the main body bracket 2 form a bracket assembly. The vertical line of the bracket assembly is in the same line as the vertical line of the aircraft. The AGV vehicle 4 spans across the bottom of the main body bracket 2 and the two wing brackets 1 along the spanwise direction, and the vertical line of the bracket assembly is located on the central axis of the AGV vehicle 4. The adapter bracket 3 can be quickly snapped into the upper part of the AGV vehicle 4 through the clamping structure set on its spanwise side, and the limiting baffle 35 arranged on the adapter bracket 3 can quickly limit the main body bracket 2 and the two wing brackets 1.

[0035] Based on the connection structure of the full-fuselage static test transfer device provided in this embodiment of the present invention, the transfer bracket 3 installed on the AGV vehicle 4 can transfer and support the bracket assembly, and the AGV vehicle 4 can precisely displace the bracket assembly and the aircraft installed on the bracket assembly.

[0036] It should be noted that the main body bracket 2 and the two wing brackets 1 in this utility model are detachably connected, and the bottom of the main body bracket 2 and the two wing brackets 1 are equipped with wheel sets, which can be moved by the towing vehicle 5.

[0037] In one implementation of this utility model, one embodiment of the main body bracket 2 is provided. Figure 2 for Figure 1 A schematic diagram of the main support frame in the full-fuselage static test transport device provided in the embodiment shown; Figure 3 for Figure 2 A schematic diagram of the vertically downward-removing ball-and-socket structure in the main bracket provided in the illustrated embodiment. (See diagram below.) Figure 2 and Figure 3 As shown, the main support frame 2 in this implementation is generally designed as a square frame structure to support the fuselage. A fixed support 21 is provided on the main load-bearing frame near the nose and near the tail of the fuselage, respectively. A set of vertically removable ball-and-socket structures 22 (e.g., ...) are symmetrically arranged on both sides of one of the fixed support frames 21 along the spanwise direction. Figure 3 As shown), the ball socket structure 22 cooperates with two process ball heads along the span of the fuselage to position and connect the aircraft fuselage; in addition, the main bracket 2 is provided with an adjustable fuselage bracket 23 at a main load-bearing frame at the nose. By adjusting the height of the adjustable fuselage bracket 23, all bracket structures in the bracket assembly can support the aircraft fuselage structure.

[0038] In a specific form of the implementation, the main body bracket 2 is provided with four rows of wheel groups along the heading, the two middle rows of wheel groups are load-bearing wheel groups 24 for displacement, the two rows of wheel groups on the two sides are anti-rollover wheel groups 25, and the anti-rollover wheel groups 25 are higher than the load-bearing wheel groups 24, so as to prevent rollover during the transfer process, and the anti-rollover wheel groups 25 can be pulled and displaced by the tractor 5.

[0039] In an implementation form of the embodiment of the utility model, an embodiment of the wing bracket 1 is provided, Figure 4 For Figure 1 The structure diagram of the main body bracket in the full fuselage static test transfer device provided in the embodiment is shown. In the implementation form, the width of the side frame of each wing bracket 1 is the same as the length of the main body bracket 2 along the heading, so as to form a quick-release connection structure with the main body bracket 2 through the side frame, and two groups of wing adjustable brackets 11 are arranged at the wing main load-bearing frame close to the fuselage side of each wing bracket 1, so as to support the wing structure on the corresponding side through adjustment of each group of wing adjustable brackets 11, and a camouflage support 12 is arranged on the wing adjustable bracket 11 located at the outer rear side, so as to support the wing in cooperation with the wing adjustable bracket 11.

[0040] In the specific implementation, four groups of load-bearing wheel groups 24 are arranged at the bottom of each wing bracket 1, and the load-bearing wheel groups 24 can be pulled and displaced by the tractor 5.

[0041] In an implementation form of the embodiment of the utility model, an embodiment of the adapter bracket 3 is provided, Figure 5 For Figure 1 The structure diagram of the adapter bracket in the full fuselage static test transfer device provided in the embodiment is shown. Referring to Figure 1 and Figure 5 In the implementation form, the main body of the adapter bracket 3 is a truss structure, and includes three groups of adapter sub-brackets, that is, one main adapter bracket 32 located in the middle and two groups of wing adapter brackets 31 located on the two sides of the main adapter bracket 32.

[0042] The wedge pressing structure 33 is arranged on both sides of the body adapter bracket 32 and the two groups of wing adapter brackets 31 along the vehicle body of the AGV 4, the wedge block 34 is pressed into the wedge pressing structure 33, the adapter bracket 3 can be quickly fixed with the AGV 4, and the limiting baffle 35 with a handle is arranged around the body adapter bracket 32 and the two groups of wing adapter brackets 31, the limiting baffle 35 is provided with three connecting holes arranged in a regular triangle at the lower part, before the body bracket 2 and the wing bracket 1 are installed, only the middle connecting hole 36 of the limiting baffle 35 is connected with the truss structure of the adapter bracket 3, and the limiting baffle 35 is rotated to the lowest position; when the body bracket 2 and the wing bracket 1 are erected on the wing adapter bracket 31 and the body adapter bracket 32, the limiting baffle 35 is rotated to the highest position around the middle connecting hole 36, the lower two connecting holes 37 are fixedly connected with the truss, and then the body bracket 2 and the wing bracket 1 are clamped on the adapter bracket 3, and are clamped between the limiting baffles 35.

[0043] It should be noted that the AGV 4 in the embodiment of the utility model is used for road transportation of the whole machine bracket. In addition, the tractor 5 is used for moving the split wing bracket 1 and the body bracket 2 respectively after the installation of the test facility is completed.

[0044] The full-body static test transfer device provided in the embodiment of the utility model solves the problems that the aircraft without landing gears is accurately transported from a manufacturing unit to a test unit, the test specified position and the test facility installation cooperation. The full-body static test transfer device provided in the utility model can realize the quick fixing between the common AGV 4 and the bracket assembly by using the wedge pressing structure of the adapter bracket 3, can realize the quick clamping between the bracket assembly and the adapter bracket 3 by using the switching of the lowest position and the highest position of the limiting baffle 35 of the adapter bracket 3, can meet the space requirement of the test site by using the combinable and split wing bracket 1 and body bracket 2, can realize the accurate positioning and reliable positioning of the aircraft on the body bracket 1 by using the combination of the fixed bracket 21, the fuselage adjustable bracket 23 and the vertically downward ball socket structure 22, and can guarantee the transportation and rollover in the transportation process by using the different heights of the wheel groups in the body bracket 1. The full-body static test transfer device provided in the embodiment of the utility model has the advantages of simple structure, low cost, convenient installation and disassembly, reusability, transportation safety guarantee and direct popularization to all whole machine transportation technical fields.

[0045] Based on the full-body static test transfer device provided in the above embodiment of the utility model, the embodiment of the utility model further provides a transfer method for performing the full-body static test process of the aircraft by using the full-body static test transfer device, and the transfer method comprises the following steps:

[0046] Step 1, the transfer bracket 3 is fixed on the AGV car 4 through the wedge-shaped compression structure 33 and the wedge-shaped block 34 in turn, at this time, the limiting baffle 35 is located at the lowest position;

[0047] Step 2, the wing bracket 1 is connected with the main bracket 2 to form a bracket assembly, the whole fuselage is hoisted on the bracket assembly, the two spread process ball heads on the airplane are placed in the ball socket structure 22 on the main bracket 2 of the bracket assembly, the airplane is positioned on the bracket assembly, it is ensured that the position supported by the bracket assembly is located on the main bearing frame of the airplane, the airplane is bound by using the tension belt, the fuselage adjustable bracket 23 located at the nose position is adjusted, so that all the brackets in the bracket assembly support the airplane structure;

[0048] Step 3, the AGV car 4 with the transfer bracket 3 is lowered to the lowest position, and is accurately shifted into the bottom of the bracket assembly, so that the wing transfer bracket 31 is located directly below the wing bracket 1, and the main body transfer bracket 32 is located directly below the main bracket 2;

[0049] Step 4, the AGV car 4 is raised to contact the bottom end surface of the bracket assembly until the bracket assembly is lifted to a certain distance from the ground;

[0050] Step 5, after rotating the limiting baffle 35 around the axis of the middle connecting hole 36 to the highest position, the two connecting holes 37 at the lowest position of the limiting baffle 35 are fixed, the limiting baffle 35 is fixed, the fixing of all the limiting baffles 35 is sequentially completed, and the bracket assembly is clamped on the transfer bracket 3;

[0051] Step 6, the camouflage support 12 is installed, the cover cloth is laid and fixed;

[0052] Step 7, the AGV car 4 is driven, and the whole fuselage is transferred to the designated position of the test site;

[0053] Step 8, after the AGV car 4 is lowered to the lowest position and the bracket assembly is placed on the ground of the test site, the AGV car 4 leaves the test site;

[0054] Step 9, after all the columns and other facilities in the test site are installed and fixed, the whole fuselage is lifted, at this time, the wing bracket 1 and the main bracket 2 are separated, and the wing bracket 1 and the main bracket 2 are sequentially removed from the test site through the column gap by using the tractor 5, thus the transfer task of the whole device is completed.

[0055] Although the embodiments disclosed by the utility model are as above, the content is only the adopted embodiment for facilitating understanding of the utility model, and is not used to limit the utility model. Any person skilled in the art of the utility model can make any modification and change on the implementation form and details without departing from the spirit and range of the utility model disclosed, but the patent protection range of the utility model still needs to be limited by the range defined by the attached claim.

Claims

1. A full fuselage static test transport device, characterized in that, It comprises: Two sets of wing brackets (1), a main bracket (2), an adapter bracket (3), an AGV vehicle (4), and a tractor (5); Among them, the two sets of wing brackets (1) are symmetrically arranged on both sides of the main bracket (2), arranged according to the shape of the aircraft, and the main bracket (2) and the two wing brackets (1) on both sides form a bracket assembly through detachable connection; the plumb line of the bracket assembly is collinear with the plumb line of the aircraft; the AGV vehicle (4) is transversely arranged on the bottom of the main bracket (2) and the two wing brackets (1) along the span, and the plumb line of the bracket assembly is located on the central axis of the AGV vehicle (4); The adapter bracket (3) is quickly clamped on the upper part of the AGV vehicle (4) through the pressing structure arranged on the spanwise side, and the adapter bracket (3) is quickly limited through the limiting baffle (35) arranged thereon, so that the adapter bracket (3) installed on the AGV vehicle (4) is used to support the bracket assembly, and the AGV vehicle (4) is used to accurately displace the bracket assembly and the aircraft installed on the bracket assembly; The bottom of the main bracket (2) and the two wing brackets (1) is provided with a wheel set for displacement under the dragging of the tractor (5).

2. The full-fuselage static test transfer device according to claim 1, wherein The main bracket (2) is integrally arranged as a square frame structure for bearing the aircraft fuselage, and fixed brackets (21) are arranged on the main bearing frames near the nose and the tail of the fuselage, respectively, and one of the fixed brackets (21) is symmetrically provided with a group of vertically downward removable ball socket structures (22) on both sides along the span for positioning and connecting the aircraft fuselage in cooperation with the two process ball heads below the fuselage along the span; The main bracket (2) is provided with a fuselage adjustable bracket (23) on the main bearing frame at the nose position, which is used to adjust the height position of the fuselage adjustable bracket (23) to make all the bracket structures in the bracket assembly support the aircraft body structure.

3. The full-fuselage static test transport apparatus of claim 2, wherein, The main bracket (2) is provided with four rows of wheel sets along the heading, the middle two rows of wheel sets are bearing wheel sets (24) for displacement, the front and rear two rows of wheel sets along the heading are anti-rollover wheel sets (25), and the anti-rollover wheel sets (25) are higher than the bearing wheel sets (24) to prevent rollover during the transfer process.

4. The full-fuselage static test transfer device according to claim 1, wherein The frame width of each side of the wing bracket (1) is the same as the length of the main bracket (2) along the heading, which is used to form a quick-release connection structure with the main bracket (2); the wing bracket (1) is provided with two groups of wing adjustable brackets (11) at the wing main bearing frame near the fuselage side, which are used to support the wing structure on each side by adjusting the wing adjustable bracket (11); the wing adjustable bracket (11) located at the outer rear side is provided with a camouflage support (12) for supporting the wing in cooperation with the wing adjustable bracket (11); the bottom of each side of the wing bracket (1) is provided with four groups of bearing wheel sets (24).

5. The full-fuselage static test transport apparatus of any one of claims 1-4, wherein, The adapter bracket is integrally provided as a truss structure, comprising three groups of adapter sub-brackets, one main adapter bracket (32) located in the middle, and two groups of wing adapter brackets (31) located on both sides of the main adapter bracket (32); Wherein, the three groups of adapter sub-brackets and the AGV vehicle (4) are quickly fixed through the wedge-shaped compression structure (33) and the wedge-shaped block (34) used in cooperation; The three groups of adapter sub-brackets and the bracket assembly are clamped and fixed through the limiting baffle (35) installed on each group of adapter sub-brackets.

6. The full-fuselage static test transport apparatus of claim 5, wherein, The main adapter bracket (32) and the two groups of wing adapter brackets (31) are provided with wedge-shaped compression structures (33) along the vehicle body of the AGV vehicle (4) on both sides in the span direction, and the adapter bracket (3) and the AGV vehicle (4) are quickly fixed by pressing the wedge-shaped block (34) in the wedge-shaped compression structure (33); The main adapter bracket (32) and the two groups of wing adapter brackets (31) are provided with limiting baffles (35) with handles around, the lower part of the limiting baffle (35) is provided with three connecting holes arranged in an equilateral triangle, before the main bracket (2) and the two side wing brackets (1) are installed, the middle connecting hole (36) of the limiting baffle (35) is connected with the truss structure of the adapter bracket (3), and the limiting baffle (35) is rotated to the lowest position; when the main bracket (2) and the two side wing brackets (1) are erected after the wing adapter bracket (31) and the main adapter bracket (32), the limiting baffle (35) is rotated to the highest position after the middle connecting hole (36), and then the main bracket (2) and the two side wing brackets (1) are clamped and fixed on the adapter bracket (3) by fixing the lower two connecting holes (37) and the truss.

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