A multi-dimensional mechanical boundary simulation and complex load applying device for a fuselage

Abstract

The application provides a fuselage multidimensional 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 docking end frame connected with a fuselage test piece, used for applying constraint boundary simulation of the front end of the fuselage test piece and transferring the applied load; a constraint boundary simulation system connected with the docking end frame, used for providing the fuselage test piece with vertical constraint of full aircraft test and vertical and lateral constraint of the main landing gear connection area test; a complex load applying system connected with the docking end frame, used for mechanically loading the fuselage test piece, simulating the load of the aircraft head boundary and applying the bending-shearing-torsion composite load in the test; and a protection system supporting the docking end frame, used for protecting the fuselage test piece in the test.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of aircraft structure static or fatigue test, and particularly relates to a fuselage multidimensional mechanical boundary simulation and complex load applying device. BACKGROUND

[0002] A new model aircraft usually needs to complete hundreds of tests according to a block test system, including element-level tests, wallboard-level tests, component-level tests, part-level tests and full aircraft-level tests. The large part test is the last step of the part-level test, which is used for preliminary investigation before full aircraft test. Through the large part test, the force transmission characteristics of the test piece new structure can be found out, data support for test finite element modeling and analysis is provided, and the weak links of the new structure design are exposed in time, which is of great significance to the manufacture of the full aircraft test machine.

[0003] The large part test is generally divided into front fuselage test, middle fuselage test, rear fuselage test and combination test. In the combination test and middle fuselage test, the nose part is generally removed to save cost. The test piece is fixed on the bearing wall through the design of a special transition section. Due to the influence of the transition section structure stiffness and the bearing wall butt joint clamp stiffness, the load transmission in the test may not be consistent with the actual force transmission of the structure, so that the real structure transmission characteristics of the test piece cannot be accurately obtained, and the test load cannot be monitored. In order to avoid this situation, the large part test needs to use full aircraft suspension support, which can judge the accuracy of the test load application by monitoring the feedback of the load in the test. Therefore, a special fuselage front end test device needs to be designed in the test, which can apply the test load of the missing part of the nose on one hand, and on the other hand, the front landing gear cannot be installed due to the lack of the nose, so a special test device is needed to simulate the constraint boundary in the test.

[0004] However, in the large part test, the test device for the nose part cannot meet the complex load application of the front end of the nose, and cannot serve as part of the test constraint boundary. SUMMARY

[0005] The purpose of the present application is to provide a fuselage multidimensional mechanical boundary simulation and complex load applying device to solve or alleviate at least one problem in the background art.

[0006] The technical solution of the present application is: a fuselage multidimensional mechanical boundary simulation and complex load applying device, comprising:

[0007] The butt joint end frame is connected with the fuselage test piece, and is used for applying the simulation of the constraint boundary of the front end of the fuselage test piece and transmitting the applied load.

[0008] A constrained boundary simulation system connected to the docking end frame for providing full aircraft test vertical constraint and main landing gear connection area test vertical and lateral constraint to the fuselage test piece;

[0009] A complex load loading system connected to the docking end frame for applying mechanical load to the fuselage test piece for simulating the load of the nose boundary and the application of the bending shear torsion composite load in the test.

[0010] A protection system supporting the docking end frame for protecting the fuselage test piece in the test.

[0011] Preferably, the docking end frame comprises 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, 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 arranged transversely on both sides of the docking end frame support box section, and the docking frame heading loading beam is arranged vertically and parallel to the middle of the docking end frame support box section.

[0013] Preferably, the constrained boundary simulation system comprises a vertical constraint simulation system and a lateral constraint simulation system, the vertical constraint simulation system further comprises an upper vertical constraint simulation system and a lower vertical constraint simulation system, the upper vertical constraint simulation system is connected to the top beam on the upper edge of the docking end frame support box section of the docking end frame, and the lower vertical constraint simulation system is connected to the load-bearing rail on the lower edge of the docking end frame support box section of the docking end frame, and the lateral constraint simulation system is connected to the docking frame lateral loading beam on the docking end frame support box section.

[0014] Preferably, the lateral constraint simulation system comprises a constraint actuator, a lateral constraint actuator base, a constraint column and a lateral constraint lug, the constraint column is fixed on the load-bearing rail, the lateral constraint actuator base is fixed on the constraint column with adjustable height, the constraint actuator is fixed on the lateral constraint actuator base, and the lateral constraint lug is arranged at the end of the constraint actuator and connected to the docking frame lateral loading beam of the docking end frame.

[0015] Preferably, the complex load loading system comprises 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 for applying complex heading load, pitch moment and yaw moment to the fuselage test piece in the test.

[0017] The lateral loading system is symmetrically arranged on the docking frame lateral loading beam with the lateral restraint simulation system, and is used for applying lateral load in the test;

[0018] The vertical loading system is connected with the lower side edge of the docking end frame support box segment and the load bearing rail, and is used for applying vertical load and roll moment to the fuselage test piece in the test.

[0019] Preferably, the heading complex load loading system comprises loading actuators, loading columns, heading loading beams and heading loading bases, the loading columns are two or more and are vertically parallel and fixed on the load bearing rail, the heading loading beams are two or more and are transversely parallel and fixed on the loading columns; at least two loading actuators are arranged on a single heading loading beam, so that multiple loading points can be formed; 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 comprises a vertical loading bottom beam, a vertical loading actuator base, a vertical loading actuator and a vertical loading double ear, the vertical loading bottom beam is fixed on the load bearing 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 double ear is installed at the end of the vertical loading actuator and connected to the lower side edge structure of the docking end frame support box segment of the docking end frame.

[0021] Preferably, the heading complex load loading system applies complex load to the fuselage test piece by combining the forces of one or more loading actuators in the heading complex load loading system.

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

[0023] The fuselage multidimensional mechanical boundary simulation and complex load applying device provided by the application solves the problems of fuselage multidimensional mechanical boundary simulation and complex load applying in large component testing, has high bearing capacity, high stability, and multiple functions, can meet the requirements of large component testing, and has low machining cost and good assembly effect. BRIEF DESCRIPTION OF DRAWINGS

[0024] In order to more clearly illustrate the technical solutions provided by the application, the drawings will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the application.

[0025] Figure 1 The figure is a schematic diagram of the fuselage multidimensional mechanical boundary simulation and complex load applying device in the application.

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

[0027] Figure 3 The figure is a schematic diagram of the constraint boundary simulation system in the application.

[0028] Figure 4 The figure is a schematic diagram of the vertical constraint simulation system in the application.

[0029] Figure 5 The figure is a schematic diagram of the upper vertical constraint base in the application.

[0030] Figure 6 The figure is a schematic diagram of the upper vertical constraint lever in the application.

[0031] Figure 7 The figure is a schematic diagram of the upper tension nut in the application.

[0032] Figure 8 The figure is a schematic diagram of the upper vertical constraint pull plate in the application.

[0033] Figure 9 The figure is a schematic diagram of the lateral constraint simulation system in the application.

[0034] Figure 10 The figure is a schematic diagram of the lateral constraint actuating cylinder base in the application.

[0035] Figure 11 The figure is a schematic diagram of the lateral actuating cylinder in the application.

[0036] Figure 12 The figure is a schematic diagram of the lateral constraint single ear in the application.

[0037] Figure 13Complex load loading system in the present application.

[0038] Figure 14 Complex load loading system in the present application.

[0039] Figure 15 Complex load loading system in the present application.

[0040] Figure 16 Complex load loading system in the present application.

[0041] Figure 17 Complex load loading system in the present application.

[0042] Figure 18 Complex load loading system in the present application.

[0043] Figure 19 Complex load loading system in the present application.

[0044] Figure 20 Complex load loading system in the present application.

[0045] Figure 21 Complex load loading system in the present application.

[0046] Figure 22 Complex load loading system in the present application.

[0047] Figure 23 Complex load loading system in the present application.

[0048] Reference signs:

[0049] 10-Butt end frame

[0050] 11-Butt plate

[0051] 12-Butt end frame support box segment

[0052] 13-Butt frame lateral load beam

[0053] 14-Butt frame heading load beam

[0054] 20-Confinement boundary simulation system

[0055] 21-Vertical confinement simulation system

[0056] 211-Upper vertical confinement simulation system

[0057] 2111-Upper vertical confinement base

[0058] 2112-Upper turnbuckle

[0059] 2113 - upper vertical restraint lever

[0060] 2114 - upper vertical restraint tie plate

[0061] 2115 - lower sensor

[0062] 212 - lower vertical restraint simulation system

[0063] 2121 - lower vertical restraint base

[0064] 2122 - lower turnbuckle

[0065] 2123 - lower vertical restraint lever

[0066] 2124 - lower vertical restraint tie plate

[0067] 2125 - lower sensor

[0068] 22 - lateral restraint simulation system

[0069] 221 - restraint ram

[0070] 2211 - ram piston rod

[0071] 2212 - ram barrel

[0072] 2213 - ram base

[0073] 222 - lateral restraint ram base

[0074] 223 - restraint column

[0075] 224 - lateral loading clevis

[0076] 2241 - clevis body

[0077] 2242 - knuckle bearing

[0078] 30 - complex load loading system

[0079] 31 - heading complex load loading system

[0080] 311 - loading ram

[0081] 312 - loading column

[0082] 313 - heading loading beam

[0083] 314 - heading loading base

[0084] 32 - lateral loading system

[0085] 33 - vertical loading system

[0086] 331 - vertically loaded bottom beam

[0087] 332 - vertically loaded actuator cylinder base

[0088] 333 - vertically loaded actuator cylinder

[0089] 334 - vertically loaded double ear

[0090] 3341 - vertically loaded bearing

[0091] 40 - protection system

[0092] 41 - protection tray

[0093] 411 - tray support plate

[0094] 412 - tray rotating rod

[0095] 413 - tray support base

[0096] 42 - protection tray stand DETAILED DESCRIPTION

[0097] In order to make the purposes, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.

[0098] As shown in Figure 1 , the fuselage multi-dimension mechanical boundary simulation and complex load applying device 100 provided by the present application comprises: 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 to transfer the applied load. The constraint boundary simulation system 20 is used to provide vertical constraint of the whole machine test and vertical and lateral constraint of the main connection area test. The complex load loading system 30 is used to perform mechanical loading, which can simulate the load of the nose boundary and complete the application of the bending-shearing-torsion composite load in the test.

[0099] As shown in Figure 2 , the docking end frame 10 comprises a docking plate 11, a docking end frame support box segment 12, a docking frame lateral loading cross beam 13 and a docking frame heading loading cross beam 14. The docking plate 11 is composed of one or more metal plates and has a shape substantially the same as that of the fuselage structure. In some embodiments of the present application, the docking plate 11 can be welded by two metal plates. A plurality of bolt holes are arranged on the docking plate 11, and the rear end surface of the docking plate 11 is connected to the fuselage test piece (not shown) by bolts. The front end surface of the docking plate 11 is fixedly connected to the docking frame support box segment 12 by welding and bolt mixing connection.

[0100] In the present application, the docking frame lateral loading crossbeam 13 and the docking frame heading loading crossbeam 14 can be two or more. In the embodiment of the present application, the docking frame lateral loading crossbeam 13 and the docking frame heading loading crossbeam 14 are both two, and the two docking frame lateral loading crossbeams 13 can be fixed at both ends of the docking end frame support box section 12 through a plurality of bolts in the transverse direction, and the docking frame heading loading crossbeam 14 can be fixed in the middle of the docking end frame support box section 12 through a plurality of bolts in the vertical direction.

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

[0102] As shown in Figures 4 to 8 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 tension nut 2112, an upper vertical constraint lever 2113, an upper vertical constraint pull plate 2114, and an upper sensor 2115. The upper vertical constraint base 2111 is fixed on the beam structure at the top of the test site, the upper tension nut 2112 is connected to the upper vertical constraint lever 2113 through a bolt adjustment, the middle of the upper vertical constraint lever 2113 is provided with a single ear structure, the single ear structure is connected to the upper vertical constraint pull plate 2114 through the upper sensor 2115, and the upper vertical constraint pull plate 2114 is connected to the upper side edge structure of the docking end frame support box section 12, so as to realize the connection between the upper vertical constraint simulation system 211 and the docking end frame 10.

[0104] Similarly, the lower vertical constraint simulation system 212 includes a lower vertical constraint base 2121, a lower tension nut 2122, a lower vertical constraint lever 2123, a lower vertical constraint pull plate 2124, and a lower sensor 2125. The lower vertical constraint base 2121 is fixed on the load-bearing rail through a beam, the lower tension nut 2122 is connected to the lower vertical constraint lever 2123 through a bolt adjustment, the middle of the lower vertical constraint lever 2123 is provided with a single ear structure, the single ear structure is connected to the lower vertical constraint pull plate 2124 through the lower sensor 2125, and the lower vertical constraint pull plate 2124 is connected to the lower side edge structure of the docking end frame support box section 12, so as to realize the connection between the lower vertical constraint simulation system 212 and the docking end frame 10.

[0105] As shown in Figures 9 to 12As shown, the lateral constraint simulation system 22 comprises a constraint actuator 221, a constraint actuator base 222, a constraint column 223 and a lateral constraint lug 224. The constraint column 223 is fixed on the load-bearing rail, the constraint actuator base 222 is fixed on the constraint column 223 in a height-adjustable manner by bolts, the constraint actuator 221 is fixed on the constraint actuator base 18, and the lateral constraint lug 224 is arranged at the end of the constraint actuator 221 and connected with the docking frame lateral loading beam 13 of the docking end frame 10, so as to realize the connection between the lateral constraint simulation system 22 and the docking end frame 10.

[0106] The constraint actuator 221 comprises an actuator piston rod 2211, an actuator cylinder 2212 and an actuator base 2213. The actuator base 2213 is fixed with the constraint actuator base 222, the actuator cylinder 2212 is hinged with the actuator base 2213, and the actuator piston rod 2211 is arranged in the actuator cylinder 2212 and can slide relatively.

[0107] The lateral constraint lug 224 comprises a lug body 2241 and a joint bearing 2242. The lug body 2241 is arranged at the end of the actuator piston rod 2211, and the joint bearing 2242 is arranged in the connecting hole of the lug body 2241.

[0108] As shown in the figure, Figure 13 The complex load loading system 30 comprises a heading complex load loading system 31, a lateral loading system 32 and a vertical loading system 33.

[0109] As shown in the figure, Figures 14 to 16 The heading complex load loading system 31 comprises 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 in parallel on the load-bearing rail, and at least two heading loading beams 313 are fixed transversely and in parallel on the loading column 312, which can be combined by bolts to form a frame structure. In the embodiment shown in the figure, there are four loading columns 312 and two heading loading beams 313. The loading actuator 311 is arranged on a single heading loading beam 313 in at least two, so as to form multiple loading points. The heading loading base 314 is located at the end of the loading actuator 311, and is hinged with the loading actuator 311 through a heading loading lug. Through the heading complex load loading system 31, complex heading load, pitch moment and yaw moment can be applied to the fuselage test piece in the test.

[0110] The lateral loading system 32 has the same structure as the lateral constraint 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, and is used to apply lateral load in the test.

[0111] As shown in the figure, 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 cylinder base 332, a vertical loading cylinder 333 and a vertical loading double ear 334. The vertical loading bottom beam 331 is fixed on the bearing rail by bolts, the vertical loading cylinder base 332 is fixed on the vertical loading bottom beam 331, the vertical loading cylinder 333 is installed on the vertical loading cylinder base 332, and the vertical loading double ear 334 is installed on the end of the vertical loading cylinder 333, and the vertical loading double ear 334 is installed on the end of the vertical loading cylinder 333. The double ears are provided with vertical loading bearings 3341 between the double ears. The vertical loading double ear 334 is connected to the lower edge structure of the docking end frame support box segment 12 of the docking end frame 10, and is used to apply vertical load and roll torque to the fuselage test piece during the test.

[0112] As shown in the figure, Figures 21 to 23 The protection system 40 includes a protection tray 31 and a protection tray column 42. The protection tray 41 includes a tray support plate 411, a tray rotating rod 412 and a tray support base 413. The tray support plate 411 is arranged on the tray rotating rod 412, and the tray support plate 411 can be moved up and down by rotating the tray rotating rod 412, so as to be in contact with the lower surface of the docking end frame 10, thereby supporting the fuselage test piece. The protection tray column 42 is fixed on the bearing rail, and the tray rotating rod 412 is installed on the protection tray column 42 through the tray support base 413. The protection system 40 is mainly used for lifting, installing and dismounting the fuselage test piece before and after, and when the vertical constraint system fails during the test, the protection tray 411 protects the fuselage test piece from large movement, avoiding unintended damage to the fuselage test piece.

[0113] In this application, except for the heading loading single ear, the lateral loading single ear, the vertical loading double ear, the upper / lower vertical constraint single ear structure and the upper / lower vertical constraint base can be machined by 30CrMnSiA material, and other components can be realized by welding or bolt connection of hot-rolled groove steel or plate material with Q345 material.

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

[0115] 1) First, the docking end frame 10 and the fuselage test piece are connected by bolts under the cooperation of the lifting device;

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

[0117] 3) Remove the lifting device, 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 cross beam at the top of the test site, and fix the lower vertical constraint system 212 on the bearing rail, then install the lateral constraint simulation system 22;

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

[0119] In this application, forces 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, and torsion to the fuselage test piece.

[0120] For example in Figure 23 The diagram shown in this embodiment illustrates the action points of two loading actuators 311 arranged on a single directional loading beam 313. The action points F1 and F2 are the action points of the two loading actuators on the upper directional loading beam 313, and the action points F3 and F4 are the action points of the two loading actuators on the lower directional loading beam 313. When applying complex loads to the fuselage test piece using the loading actuator 311, the following methods can be used: Applying a pitch load to the fuselage test piece by simultaneously applying loads to points F1 and F2 while not applying loads to points F3 and F4, or simultaneously applying loads to points F3 and F4 while not applying loads to points F1 and F2; applying a yaw load to the fuselage test piece by simultaneously applying loads to points F1 and F3 while not applying loads to points F2 and F4, or simultaneously applying loads to points F2 and F4 while not applying loads to points F1 and F3; applying a torsional load to the fuselage test piece by simultaneously applying loads to points F1 and F4 while not applying loads to points F2 and F3, or simultaneously applying loads to points F2 and F3 while not applying loads to points F1 and F4; or applying complex loads to the fuselage test piece by simultaneously applying loads to points F1, F2, and F3 while not applying loads to point F4, or simultaneously applying loads to points F1, F2, and F4 while not applying loads to point F3.

[0121] The fuselage multi-dimensional mechanical boundary simulation and complex load application device of this application can constrain or apply loads to the fuselage test piece according to different working conditions during the test. The directional complex load application system 31 can meet the application requirements of drag, pitching 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 roll 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 application system 30 operate synchronously and do not interfere with each other, which can meet the requirements of multi-dimensional mechanical boundary simulation and complex load application.

[0122] The multi-dimension mechanical boundary simulation of the fuselage and the complex load applying device provided by the application efficiently solve the problems of the multi-dimension mechanical boundary simulation of the fuselage and the complex load applying in the large component test, the device has strong bearing capacity, high stability, and many functions, and can meet the requirements of the large component test, the structures or components in each system have low processing cost and good assembly effect; the device is designed in the form of three separated parts of the docking end frame 10, the constraint boundary simulation system 20, and the complex load applying system 30, has simple structure, convenient processing and installation, is easy to implement, and has good practicability and universality.

[0123] The above merely provides a specific implementation of the application, but the protection scope of the application is not limited to this, any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the application, which should be covered in the protection scope of the application. Therefore, the protection scope of the application should be subject to the protection scope of the claims.

Claims

1. A device for simulating multi-dimensional mechanical boundary conditions of a fuselage and applying complex loads, characterized by The application relates to a full-scale aircraft fuselage test system, which comprises the following parts: a docking end frame connected with a fuselage test piece and used for applying a simulated constraint boundary of a front end of the fuselage test piece and transmitting a loaded load, the docking end frame comprising 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 being connected with the fuselage test piece and the other side being connected with the docking end frame support box section, the docking frame lateral loading beam and the docking frame heading loading beam being arranged on the docking end frame support box section; a constraint boundary simulation system connected with the docking end frame and used for providing a full-scale aircraft test vertical constraint and a main landing gear connection area test vertical and lateral constraint to the fuselage test piece, the constraint boundary simulation system comprising a vertical constraint simulation system and a lateral constraint simulation system; a complex load loading system connected with the docking end frame and used for mechanically loading the fuselage test piece and simulating a load of a nose boundary and a bending shear torsion complex load in a test, the complex load loading system comprising a heading complex load loading system, a lateral loading system and a vertical loading system, the heading complex load loading system being connected with the docking frame heading loading beam in the docking end frame and used for applying a complex heading load, a pitch moment and a yaw moment to the fuselage test piece in the test, the lateral loading system being symmetrically arranged on the docking frame lateral loading beam with the lateral constraint simulation system and used for applying a lateral load in the test, and the vertical loading system being connected with a bearing rail and a lower side edge of the docking end frame support box section and used for applying a vertical load and a roll moment to the fuselage test piece in the test, wherein the heading complex load loading system comprises loading actuators, loading columns, a heading loading beam and a heading loading base, the loading columns are two or more and vertically parallel and fixed on the bearing rail, the heading loading beam is two or more and horizontally parallel and fixed on the loading columns, at least two loading actuators are arranged on a single heading loading beam so as to form multiple loading points, and the heading loading base is located at the end of the loading actuator and is hinged with the loading actuator through a heading loading single lug; a protection system supporting the docking end frame and used for protecting the fuselage test piece in the test.

2. The device of claim 1, wherein the device further comprises a plurality of actuators configured to apply a plurality of forces to the body. The docking frame lateral loading beam and the docking frame heading loading beam are two or more, the docking frame lateral loading beam is horizontally arranged on both sides of the docking end frame support box section, and the docking frame heading loading beam is vertically and parallel arranged in the middle of the docking end frame support box section.

3. The device of claim 1 or 2, wherein the device further comprises a plurality of force sensors arranged on the plurality of force applying units. The vertical constraint simulation system further comprises an upper vertical constraint simulation system and a lower vertical constraint simulation system, the upper vertical constraint simulation system being connected with a top beam and an upper side edge of the docking end frame support box section of the docking end frame, the lower vertical constraint simulation system being connected with a bearing rail and a lower side edge of the docking end frame support box section of the docking end frame, and the lateral constraint simulation system being connected with the docking frame lateral loading beam on the docking end frame support box section.

4. The device of claim 3, wherein the device further comprises a plurality of force sensors. The lateral constraint simulation system comprises a constraint actuator, a lateral constraint actuator base, a constraint column and a lateral constraint lug, the constraint column is fixed on the load-bearing rail, the lateral constraint actuator base is fixed on the constraint column in a height-adjustable manner, the constraint actuator is fixed on the lateral constraint actuator base, and the lateral constraint lug is arranged at the end of the constraint actuator and connected with the lateral loading beam of the docking end frame.

5. The device of claim 4, wherein the device further comprises a plurality of force sensors. The vertical loading system is one or more, and the vertical loading system comprises a vertical loading base beam, a vertical loading actuator base, a vertical loading actuator and a vertical loading lug, the vertical loading base beam is fixed on the load-bearing rail, the vertical loading actuator base is fixed on the vertical loading base beam, the vertical loading actuator is installed on the vertical loading actuator base, and the vertical loading lug is installed at the end of the vertical loading actuator and connected to the lower side edge structure of the docking end frame support box segment of the docking end frame.

6. The device of claim 5, wherein the device further comprises a plurality of force sensors. The heading complex load loading system is realized by combining the action force of one or more loading actuators in the heading complex load loading system, so that the heading complex load loading system can exert complex load on the fuselage test piece.

7. The device of claim 1, wherein the device further comprises a plurality of actuators configured to apply a plurality of forces to the body. The protection system comprises a protection tray and a protection tray column, the protection tray comprises a tray support plate, a tray rotating rod and a tray support base, the tray support plate is arranged on the tray rotating rod, the tray support plate can be moved up and down by rotating the tray rotating rod, so as to contact the lower surface of the docking end frame and support the fuselage test piece, the protection tray column is fixed on the load-bearing rail, and the tray rotating rod is installed on the protection tray column through the tray support base.

Images