Fuselage multi-dimensional mechanical boundary simulation and complex load applying device

Abstract

The invention provides a fuselage multi-dimensional mechanical boundary simulation and complex load applying device, and belongs to the field of aircraft structure static force or fatigue test, the device comprises a butt joint end frame, the butt joint end frame is connected with a fuselage test piece and is used for applying simulation of a constraint boundary at the front end of the fuselage test piece and transmitting of a loading load; the constraint boundary simulation system is connected with the butt joint end frame and is used for providing full-aircraft test vertical constraint and main undercarriage connection area test vertical and lateral constraint for the fuselage test piece; the complex load loading system is connected with the butt joint end frame, and is used for carrying out mechanical loading on the fuselage test piece and simulating the load of the boundary of the fuselage and the application of a bending-shear-torsion combined load in the test; and the protection system supports the butt joint end frame and is used for protecting the fuselage test piece in the test.

Description

Technical Field

[0001] The present application belongs to the field of static or fatigue testing of aircraft structures, and in particular relates to a multi-dimensional mechanical boundary simulation and complex load application device for a fuselage. Background Art

[0002] New aircraft models usually need to complete hundreds of tests based on the building block test system, including component-level tests, panel-level tests, assembly-level tests, component-level tests, and full-aircraft-level tests. Large component tests are the last step of component-level tests, which are used to conduct a preliminary investigation before full-aircraft tests. Through large component tests, the force transmission characteristics of the new structure of the test piece can be understood, providing data support for experimental finite element modeling and analysis, and timely exposing the weak links of the new structure design, which is of great significance to the manufacture of full-aircraft test machines.

[0003] The test of large components is generally divided into the front fuselage test, the middle fuselage test, the rear fuselage test and the combination test. In the combination test and the middle fuselage test, the nose part is usually removed to save costs. By designing a special transition section on the test piece, the test piece is fixed on the load-bearing wall for testing. Due to the influence of the structural stiffness of the transition section and the stiffness of the clamps docking the load-bearing wall, part of the load transfer in the test may not match the actual force transmission of the structure, so that the real structural force transmission characteristics of the test piece cannot be accurately obtained, and the application of the test load cannot be monitored. In order to avoid this situation, the large component test needs to adopt the whole aircraft suspended support, and the accuracy of the test load application can be judged by monitoring the feedback of the load in the test. Therefore, a special test device for the front end of the fuselage needs to be designed in the test. On the one hand, the test load of the missing part of the nose is applied. On the other hand, due to the lack of the nose, the front landing gear cannot be installed, and a special test device is required to simulate the constraint boundary in the test.

[0004] However, in large component testing, the test device used for the nose section cannot meet the requirements of applying complex loads at the front end of the nose and cannot serve as part of the test constraint boundary. Summary of the invention

[0005] The purpose of the present application is to provide a multi-dimensional mechanical boundary simulation and complex load application device for a fuselage to solve or alleviate at least one problem in the background technology.

[0006] The technical solution of the present application is: a device for simulating the multi-dimensional mechanical boundary of a fuselage and applying complex loads, comprising:

[0007] A butt end frame, the butt end frame being connected to the fuselage test piece and used for simulating the constraint boundary of the front end of the fuselage test piece and transferring the loading load;

[0008] A constraint boundary simulation system, the constraint boundary simulation system is connected to the docking end frame and is used to provide vertical constraints for the whole aircraft test and vertical and lateral constraints for the main landing gear connection area test to the fuselage test piece;

[0009] A complex load loading system, which is connected to the docking end frame and is used to apply mechanical loading to the fuselage test piece, to simulate the load on the nose boundary and to apply the bending, shearing and torsion composite load in the test;

[0010] A protection system supports the docking end frame and is used to protect the fuselage test piece during the test.

[0011] Preferably, the docking end frame includes a docking plate, a docking end frame support box section, a docking frame lateral loading beam and a docking frame heading loading beam, one side of the docking plate is connected to the fuselage test piece, and the other side is connected to the docking end frame support box section, and the docking frame lateral loading beam and the docking frame heading loading beam are arranged on the docking end frame support box section.

[0012] Preferably, the docking frame lateral loading beam and the docking frame heading loading beam are two or more, the docking frame lateral loading beam is transversely arranged on both sides of the docking end frame support box section, and the docking frame heading loading beam is vertically parallelly arranged in the middle of the docking end frame support box section.

[0013] Preferably, the constraint boundary simulation system includes a vertical constraint simulation system and a lateral constraint simulation system, and the vertical constraint simulation system further includes an upper vertical constraint simulation system and a lower vertical constraint simulation system, the upper vertical constraint simulation system connects the upper edge of the docking end frame support box section of the docking end frame with the top beam, the lower vertical constraint simulation system connects the lower edge of the docking end frame support box section of the docking end frame with the load-bearing ground rail, and the lateral constraint simulation system connects the docking frame lateral loading beam on the docking end frame support box section.

[0014] Preferably, the lateral restraint simulation system includes a restraint actuator, a lateral restraint actuator base, a restraint column and a lateral restraint single ear, the restraint column is fixed on the load-bearing ground rail, the lateral restraint actuator base is height-adjustably fixed on the restraint column, the restraint actuator is fixed on the lateral restraint actuator base, and the lateral restraint single ear is arranged at the end of the restraint actuator and is connected to the lateral loading beam of the docking frame of the docking end frame.

[0015] Preferably, the complex load loading system includes a heading complex load loading system, a lateral loading system and a vertical loading system;

[0016] The heading complex load loading system is connected to the docking frame heading loading beam in the docking end frame, and is used to apply complex heading loads, pitching moments and yaw moments to the fuselage test piece during the test.

[0017] The lateral loading system and the lateral restraint simulation system are symmetrically arranged on the lateral loading beam of the docking frame, and are used to apply lateral loads in the test;

[0018] The vertical loading system connects the load-bearing ground rail and the lower edge of the butt end frame support box section, and is used to apply vertical load and rolling torque to the fuselage test piece during the test.

[0019] Preferably, the heading complex load loading system includes a loading actuator, a loading column, a heading loading beam and a heading loading base, the loading columns are two or more and vertically and parallelly fixed on the load-bearing ground rail, the heading loading beams are two or more and laterally and parallelly fixed on the loading columns; at least two loading actuators are arranged on a single heading loading beam, thereby forming multiple loading points; the heading loading base is located at the end of the loading actuator, and the heading loading base is hinged to the loading actuator through a heading loading single ear.

[0020] Preferably, the vertical loading system is one or more, and the vertical loading system includes a vertical loading bottom beam, a vertical loading actuator cylinder base, a vertical loading actuator cylinder and vertical loading ears, the vertical loading bottom beam is fixed on the load-bearing ground rail, the vertical loading actuator cylinder base is fixed on the vertical loading bottom beam, the vertical loading actuator cylinder is installed on the vertical loading actuator cylinder base, and the vertical loading ears are installed at the end of the vertical loading actuator cylinder and connected to the lower edge structure of the docking end frame support box section of the docking end frame.

[0021] Preferably, the complex load is applied to the fuselage test piece by the complex load loading system in the heading direction through the combination of one or more loading actuators in the heading complex load loading system.

[0022] Preferably, the protection system includes a protection pallet and a protection pallet column, the protection pallet includes a pallet support plate, a pallet rotating rod and a pallet support base, the pallet support plate is arranged on the pallet rotating rod, and the pallet support plate can be moved up and down by rotating the pallet rotating rod, so as to contact the lower surface of the docking end frame and thus play a role in supporting the fuselage test piece, the protection pallet column is fixed on the load-bearing ground rail, and the pallet rotating rod is installed on the protection pallet column through the pallet support base.

[0023] The multi-dimensional mechanical boundary simulation and complex load application device for the fuselage provided in the present application efficiently solves the problems of multi-dimensional mechanical boundary simulation and complex load application of the fuselage in large component tests. The device has strong load-bearing capacity, high stability, and a wide range of functions, and can meet the requirements of large component tests. The structure or component processing cost of each system is low and the assembly effect is good. It adopts a three-part separate design of a docking end frame, a constraint boundary simulation system, and a complex load loading system. The structure is simple in structure, easy to process and install, easy to implement in engineering, and has good practicality and versatility. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0025] Figure 1 Schematic diagram of the multi-dimensional mechanical boundary simulation and complex load application device of the fuselage in this application.

[0026] Figure 2 This is a schematic diagram of the docking end frame in this application.

[0027] Figure 3 Schematic diagram of the constraint boundary simulation system in this application.

[0028] Figure 4 Schematic diagram of the vertical constraint simulation system in this application.

[0029] Figure 5 Schematic diagram of the upper vertical constraint base in this application.

[0030] Figure 6 It is a schematic diagram of the upper vertical restraint lever in this application;

[0031] Figure 7 It is a schematic diagram of the upper tensioning screw sleeve in this application.

[0032] Figure 8 Schematic diagram of the upper vertical restraint pull plate in this application.

[0033] Fig. 9 Schematic diagram of the lateral restraint simulation system in this application.

[0034] Fig.10 Schematic diagram of the lateral restraint actuator base in this application.

[0035] Fig.11 It is a schematic diagram of the lateral actuator in this application.

[0036] Fig.12 Schematic diagram of a laterally constrained single ear in this application.

[0037] Fig.13Schematic diagram of the complex load loading system in this application.

[0038] Fig.14 This is a schematic diagram of the heading complex load loading system in this application.

[0039] Fig.15 Schematic diagram of the heading loading beam in this application.

[0040] Fig.16 Schematic diagram of the heading loading base in this application.

[0041] Fig.17 Schematic diagram of the vertical loading system in this application.

[0042] Fig.18 Schematic diagram of the vertical loading bottom beam in this application.

[0043] Fig.19 Schematic diagram of the vertical loading actuator base in this application.

[0044] Fig. 20 This is a schematic diagram of the vertically loaded binaural system in this application.

[0045] Fig.21 This is a schematic diagram of the protection system in this application.

[0046] Fig. 22 This is a schematic diagram of the combination of the protection tray and the protection tray column in this application.

[0047] Fig.23 Schematic diagram of the loading actuator action point in this application.

[0048] Reference numerals:

[0049] 10-Butt end frame

[0050] 11- Docking plate

[0051] 12-Butt end frame support box segment

[0052] 13-Docking frame side loading beam

[0053] 14- Docking frame heading loading beam

[0054] 20-Constrained Boundary Simulation System

[0055] 21-Vertical Constraint Simulation System

[0056] 211-Vertical Constraint Simulation System

[0057] 2111-Upper vertical restraint base

[0058] 2112-Top elastic nut

[0059] 2113-Upper vertical restraint lever

[0060] 2114-Upper vertical restraint plate

[0061] 2115-Lower sensor

[0062] 212-Downward Constraint Simulation System

[0063] 2121-drooping restraint base

[0064] 2122-Lower elastic thread sleeve

[0065] 2123-Sagittal restraint lever

[0066] 2124-Downward restraint plate

[0067] 2125-Lower sensor

[0068] 22-Lateral restraint simulation system

[0069] 221-Constraint Actuator

[0070] 2211-Actuator piston rod

[0071] 2212-Actuator Cylinder

[0072] 2213-Actuator base

[0073] 222-Lateral restraint actuator base

[0074] 223-Constraint Column

[0075] 224-Side loading single ear

[0076] 2241-Single ear body

[0077] 2242-Spherical bearing

[0078] 30-Complex load loading system

[0079] 31-Heading complex load loading system

[0080] 311-Loading Actuator

[0081] 312-Loading column

[0082] 313-Heading loading beam

[0083] 314-Heading loading base

[0084] 32-Side loading system

[0085] 33-Vertical loading system

[0086] 331-Vertical loading bottom beam

[0087] 332-Vertical Loading Actuator Base

[0088] 333-Vertical Loading Actuator

[0089] 334-Vertical loading double ears

[0090] 3341-Vertical Loaded Bearing

[0091] 40-Protection System

[0092] 41-Protect the tray

[0093] 411-Pallet support plate

[0094] 412-Pallet Rotating Rod

[0095] 413-Tray support base

[0096] 42-Protective pallet columns DETAILED DESCRIPTION

[0097] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0098] like Figure 1 As shown, the fuselage multi-dimensional mechanical boundary simulation and complex load application device 100 provided in the present application includes: a docking end frame 10, a constraint boundary simulation system 20, a complex load loading system 30 and a protection system 40. The docking end frame 10 is used to simulate the constraint boundary of the front end of the fuselage and transfer the loading load. The constraint boundary simulation system 20 provides vertical constraints for the entire aircraft test and vertical and lateral constraints for the main starting connection area test. Mechanical loading is performed through the complex load loading system 30, which can simulate the load on the nose boundary and complete the application of the combined bending, shear and torsion loads in the test.

[0099] like Figure 2 As shown, the docking end frame 10 includes a docking plate 11, a docking end frame support box section 12, a docking frame lateral loading beam 13 and a docking frame heading loading beam 14. Among them, the docking plate 11 is composed of one or more metal plates, and has a shape roughly the same as the fuselage structure. In some embodiments of the present application, the docking plate 11 can be welded from two metal plates, and one or more circles of bolt holes are set on the docking plate 11, and its rear end face is connected to the fuselage test piece (not shown) by bolts. The front end face of the docking plate 11 can be fixedly connected to the docking frame support box section 12 by a mixed connection method of welding and bolts.

[0100] In the present application, the docking frame lateral loading beam 13 and the docking frame course loading beam 14 can be two or more. In this embodiment of the present application, the docking frame lateral loading beam 13 and the docking frame course loading beam 14 are both two, and the two docking frame lateral loading beams 13 can be transversely fixed to the two ends of the docking end frame support box section 12 by multiple bolts, and the docking frame course loading beam 14 can be vertically and parallelly fixed to the middle of the docking end frame support box section 12 by multiple bolts.

[0101] like Figure 3 As shown, the constraint boundary simulation system 20 includes a vertical constraint simulation system 21 and a lateral constraint simulation system 22 .

[0102] Combination Figures 4 to 8 As shown, the vertical constraint simulation system 21 includes an upper vertical constraint simulation system 211 and a lower vertical constraint simulation system 212 .

[0103] The upper vertical constraint simulation system 211 includes an upper vertical constraint base 2111, an upper turnbuckle 2112, an upper vertical constraint lever 2113, an upper vertical constraint plate 2114 and an upper sensor 2115. The upper vertical constraint base 2111 is fixed on the crossbeam structure at the top of the test site, the upper turnbuckle 2112 is adjustably connected to the upper vertical constraint base 2111 and the upper vertical constraint lever 2113 by bolts, a single ear structure is provided in the middle of the upper vertical constraint lever 2113, the single ear structure is connected to the upper vertical constraint plate 2114 through the upper sensor 2115, and the upper vertical constraint plate 2114 is connected to the upper side edge structure of the docking end frame support box section 12, thereby realizing the connection between the upper vertical constraint simulation system 211 and the docking end frame 10.

[0104] Similarly, the droop constraint simulation system 212 includes a droop constraint base 2121, a lower turnbuckle 2122, a droop constraint lever 2123, a droop constraint plate 2124 and a lower sensor 2125. The droop constraint base 2121 is fixed on the load-bearing ground rail through a crossbeam, the lower turnbuckle 2122 is adjustable by bolts to connect the droop constraint base 2121 and the droop constraint lever 2123, a single ear structure is provided in the middle of the droop constraint lever 2123, the single ear structure is connected to the droop constraint plate 2124 through the lower sensor 2125, and the droop constraint plate 2124 is connected to the lower side edge structure of the docking end frame support box section 12, thereby realizing the connection between the droop constraint simulation system 212 and the docking end frame 10.

[0105] like Figures 9 to 12As shown, the lateral restraint simulation system 22 includes a restraint actuator 221, a lateral restraint actuator base 222, a restraint column 223 and a lateral restraint single ear 224. The restraint column 223 is fixed on the load-bearing ground rail, the lateral restraint actuator base 222 is fixed on the restraint column 223 by bolts with adjustable height, the restraint actuator 221 is fixed on the lateral restraint actuator base 18, and the lateral restraint single ear 224 is arranged at the end of the restraint actuator 221 and connected to the docking frame lateral loading beam 13 of the docking end frame 10, thereby realizing the connection between the lateral restraint simulation system 22 and the docking end frame 10.

[0106] Among them, the constraint actuator 221 includes an actuator piston rod 2211, an actuator body 2212 and an actuator base 2213. The actuator base 2213 is fixed to the lateral constraint actuator base 222. The actuator body 2212 is hinged to the actuator base 2213. The actuator piston rod 2211 is arranged in the actuator body 2212 and can slide relatively.

[0107] The lateral restraining single ear 224 includes a single ear body 2241 and a joint bearing 2242 . The single ear body 2241 is arranged at the end of the piston rod 2211 of the actuator cylinder, and the joint bearing 2242 is arranged in the connecting hole of the single ear body 2241 .

[0108] like Fig.13 As shown, the complex load loading system 30 includes a heading complex load loading system 31 , a lateral loading system 32 and a vertical loading system 33 .

[0109] like Figures 14 to 16 As shown, the heading complex load loading system 31 includes a loading actuator 311, a loading column 312, a heading loading beam 313 and a heading loading base 314. Two or more loading columns 312 are fixed vertically and parallelly on the load-bearing ground rail, and at least two heading loading beams 313 are fixed horizontally and parallelly on the loading columns 312, and the two can be combined by bolts to form a frame structure. In the illustrated embodiment of the present application, there are four loading columns 312 and two heading loading beams 313. At least two loading actuators 311 are arranged on a single heading loading beam 313, so that multiple loading points can be formed. The heading loading base 314 is located at the end of the loading actuator 311, and is hinged to the loading actuator 311 through a heading loading single ear. The heading complex load loading system 31 can apply complex heading loads, pitch moments and yaw moments to the fuselage test piece during the test.

[0110] The lateral loading system 32 has the same structure as the lateral restraint simulation system 22 and is symmetrically arranged on the docking frame lateral loading beam 13 on the other side of the docking end frame 10 to apply lateral loads in the test.

[0111] like Figures 17 to 20As shown, the vertical loading system 33 is one or more, which includes a vertical loading bottom beam 331, a vertical loading actuator base 332, a vertical loading actuator 333 and vertical loading ears 334. The vertical loading bottom beam 331 is fixed to the load-bearing ground rail by bolts, the vertical loading actuator base 332 is fixed to the vertical loading bottom beam 331, the vertical loading actuator 333 is installed on the vertical loading actuator base 332, and the vertical loading ears 334 are installed at the end of the vertical loading actuator 333, and a vertical loading bearing 3341 is arranged between the ears. The vertical loading ears 334 are connected to the lower edge structure of the docking end frame support box section 12 of the docking end frame 10, and are used to apply vertical load and rolling torque to the fuselage test piece during the test.

[0112] like Figure 21 to Figure 23 As shown, the protection system 40 includes a protection pallet 31 and a protection pallet column 42. The protection pallet 41 includes a pallet support plate 411, a pallet rotating rod 412 and a pallet support base 413. The pallet support plate 411 is arranged on the pallet rotating rod 412, and the pallet support plate 411 can be moved up and down by rotating the pallet rotating rod 412, so as to contact with the lower surface of the docking end frame 10, thereby playing a role in supporting the fuselage test piece. The protection pallet column 42 is fixed on the load-bearing ground rail, and the pallet rotating rod 412 is installed on the protection pallet column 42 through the pallet support base 413. The protection system 40 is mainly used for front and rear lifting, installation and disassembly of the fuselage test piece, and when a problem occurs in the vertical restraint system during the test, the protection pallet 411 is used to protect the fuselage test piece from large movement, thereby avoiding unexpected damage to the fuselage test piece.

[0113] In the present application, except for the heading loading single ear, lateral loading single ear, vertical loading double ears, upper / lower vertical constraint single ear structure and upper / lower vertical constraint base which can be machined from 30CrMnSiA material, all other components can be made of hot-rolled channel steel or plate made of Q345 by welding or bolting.

[0114] The installation process of the fuselage multi-dimensional mechanical boundary simulation and complex load application device of this application is as follows:

[0115] 1) With the help of the lifting device, firstly connect the butt end frame 10 and the fuselage test piece with bolts;

[0116] 2) Fix the protection system 40 on the load-bearing ground rail, and rotate the protection tray 41 to contact the lower surface of the docking end frame 10;

[0117] 3) Remove the lifting device and install the vertical constraint simulation system 21 in the constraint boundary simulation system 20. First, fix the upper vertical constraint simulation system 211 on the beam at the top of the test site, fix the lower vertical constraint system 212 on the load-bearing ground rail, and then install the lateral constraint simulation system 22;

[0118] 4) According to the test requirements, the complex load loading system 30 is fixed on the load-bearing ground rail.

[0119] In the present application, the force can be applied by combining one or more loading actuators 311 in the heading complex load loading system 31, so that the heading complex load loading system 31 can apply complex force conditions such as heading, pitch, yaw, torsion, etc. to the fuselage test piece.

[0120] For example, Fig.23 The schematic diagram of the action points of two loading actuators 311 arranged on a single heading loading beam 313 in the embodiment of the present application is shown, wherein the action points F1 and F2 are the two action points of the loading actuators on the upper heading loading beam 313, and the action points F3 and F4 are the two action points of the loading actuators on the lower heading loading beam 313. When a complex load is applied to the fuselage test piece by loading the actuator 311, the pitch load of the fuselage test piece can be applied by applying the action points F1 and F2 at the same time and not applying the load to the action points F3 and F4, or by applying the action points F3 and F4 at the same time and not applying the load to the action points F1 and F2; the yaw load of the fuselage test piece can be applied by applying the action points F1 and F3 at the same time and not applying the load to the action points F2 and F4, or by applying the action points F2 and F4 at the same time and not applying the load to the action points F1 and F3; the torsion load of the fuselage test piece can be applied by applying the action points F1 and F4 at the same time and not applying the load to the action points F2 and F3, or by applying the action points F2 and F3 at the same time and not applying the load to the action points F1 and F4; or the complex load of the fuselage test piece can be applied by applying the action points F1, F2 and F3 at the same time and not applying the load to the action point F4, or by applying the action points F1, F2 and F4 at the same time and not applying the load to the action point F3.

[0121] The fuselage multi-dimensional mechanical boundary simulation and complex load application device of the present application can constrain or apply loads to the fuselage test piece according to different working conditions during the test. The heading complex load loading system 31 can meet the application requirements of resistance, pitch moment and yaw moment, etc. The lateral loading system 32 can meet the application requirements of yaw moment, the vertical loading system 33 can meet the application requirements of lift and rolling moment, and the constraint boundary simulation system 20 can meet the vertical constraint and lateral constraint. During the test, the constraint boundary simulation system 20 and the complex load loading system 30 run synchronously without interfering with each other, which can meet the requirements of multi-dimensional mechanical boundary simulation and complex load application.

[0122] The multi-dimensional mechanical boundary simulation and complex load application device for the fuselage provided in the present application efficiently solves the problems of multi-dimensional mechanical boundary simulation and complex load application for the fuselage in large component tests. The device has strong load-bearing capacity, high stability, and a wide range of functions, and can meet the requirements of large component tests. The structure or component processing cost of each system is low and the assembly effect is good. It adopts a three-part separate design of a docking end frame 10, a constraint boundary simulation system 20, and a complex load loading system 30, with a simple structure, convenient processing and installation, easy engineering implementation, and good practicality and versatility.

[0123] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A device for multi-dimensional mechanical boundary simulation and complex load application of fuselage, characterized in that: include: A butt end frame, the butt end frame being connected to the fuselage test piece and used for simulating the constraint boundary of the front end of the fuselage test piece and transferring the loading load; A constraint boundary simulation system, the constraint boundary simulation system is connected to the docking end frame and is used to provide vertical constraints for the whole aircraft test and vertical and lateral constraints for the main landing gear connection area test to the fuselage test piece; A complex load loading system, which is connected to the docking end frame and is used to apply mechanical loading to the fuselage test piece, to simulate the load on the nose boundary and to apply the bending, shearing and torsion composite load in the test; A protection system supports the docking end frame and is used to protect the fuselage test piece during the test.

2. The fuselage multi-dimensional mechanical boundary simulation and complex load application device according to claim 1, characterized in that: The docking end frame includes a docking plate, a docking end frame support box section, a docking frame lateral loading beam and a docking frame heading loading beam. One side of the docking plate is connected to the fuselage test piece, and the other side is connected to the docking end frame support box section. The docking frame lateral loading beam and the docking frame heading loading beam are arranged on the docking end frame support box section.

3. The fuselage multi-dimensional mechanical boundary simulation and complex load application device according to claim 2, characterized in that: The docking frame has two or more lateral loading beams and directional loading beams. The lateral loading beams are arranged transversely on both sides of the docking end frame support box section, and the directional loading beams are arranged vertically and parallelly in the middle of the docking end frame support box section.

4. The fuselage multi-dimensional mechanical boundary simulation and complex load application device according to claim 2 or 3, characterized in that: The constraint boundary simulation system includes a vertical constraint simulation system and a lateral constraint simulation system. The vertical constraint simulation system further includes an upper vertical constraint simulation system and a lower vertical constraint simulation system. The upper vertical constraint simulation system connects the upper edge of the docking end frame support box section of the docking end frame with the top beam, the lower vertical constraint simulation system connects the lower edge of the docking end frame support box section of the docking end frame with the load-bearing ground rail, and the lateral constraint simulation system connects the docking frame lateral loading beam on the docking end frame support box section.

5. The fuselage multi-dimensional mechanical boundary simulation and complex load application device according to claim 4, characterized in that: The lateral restraint simulation system includes a restraint actuator, a lateral restraint actuator base, a restraint column and a lateral restraint single ear, wherein the restraint column is fixed on a load-bearing ground rail, the lateral restraint actuator base is height-adjustably fixed on the restraint column, the restraint actuator is fixed on the lateral restraint actuator base, and the lateral restraint single ear is arranged at the end of the restraint actuator and connected to the lateral loading beam of the docking frame of the docking end frame.

6. The fuselage multi-dimensional mechanical boundary simulation and complex load application device according to claim 5, characterized in that: The complex load loading system includes a heading complex load loading system, a lateral loading system and a vertical loading system; The heading complex load loading system is connected to the docking frame heading loading beam in the docking end frame, and is used to apply complex heading loads, pitching moments and yaw moments to the fuselage test piece during the test. The lateral loading system and the lateral restraint simulation system are symmetrically arranged on the lateral loading beam of the docking frame, and are used to apply lateral loads in the test; The vertical loading system connects the load-bearing ground rail and the lower edge of the butt end frame support box section, and is used to apply vertical load and rolling torque to the fuselage test piece during the test.

7. The fuselage multi-dimensional mechanical boundary simulation and complex load application device according to claim 6, characterized in that: The heading complex load loading system includes a loading actuator, a loading column, a heading loading beam and a heading loading base. The loading columns are two or more and vertically and parallelly fixed on the load-bearing ground rail, and the heading loading beams are two or more and laterally and parallelly fixed on the loading columns. At least two loading actuators are arranged on a single heading loading beam, thereby forming multiple loading points. The heading loading base is located at the end of the loading actuator, and the heading loading base is hinged to the loading actuator through a heading loading single ear.

8. The fuselage multi-dimensional mechanical boundary simulation and complex load application device according to claim 6, characterized in that: The vertical loading system is one or more, and the vertical loading system includes a vertical loading bottom beam, a vertical loading actuator base, a vertical loading actuator and vertical loading ears. The vertical loading bottom beam is fixed on the load-bearing ground rail, the vertical loading actuator base is fixed on the vertical loading bottom beam, the vertical loading actuator is installed on the vertical loading actuator base, and the vertical loading ears are installed at the end of the vertical loading actuator and connected to the lower edge structure of the docking end frame support box section of the docking end frame.

9. The fuselage multi-dimensional mechanical boundary simulation and complex load application device according to claim 7, characterized in that: The complex load application of the heading complex load loading system to the fuselage test piece is achieved by applying a force in combination with one or more loading actuators in the heading complex load loading system.

10. The fuselage multi-dimensional mechanical boundary simulation and complex load application device according to claim 2, characterized in that: The protection system includes a protection pallet and a protection pallet column. The protection pallet includes a pallet support plate, a pallet rotating rod and a pallet support base. The pallet support plate is arranged on the pallet rotating rod. The pallet supporting plate can be moved up and down by rotating the pallet rotating rod, so as to contact the lower surface of the docking end frame and thus play a role in supporting the fuselage test piece. The protection pallet column is fixed on the load-bearing ground rail, and the pallet rotating rod is installed on the protection pallet column through the pallet support base.

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