A boundary simulation support device for boarding door strength testing

Abstract

This application provides a boundary simulation support device for boarding door strength testing, belonging to the field of aircraft door testing. The device includes: a test frame; a boarding door test piece for simulating a boarding door; a fuselage skin adapter assembly connecting the boarding door test piece and a boundary stiffness active control system, used to transfer the boundary stiffness generated by the boundary stiffness active control system to the boarding door test piece; and a boundary stiffness active control system, mounted on the test frame and connected to the fuselage skin adapter assembly, used to generate adjustable boundary stiffness, supporting the boarding door test piece through the boundary stiffness, thus achieving simulated support for the boarding door boundary stiffness. The boundary simulation support device for boarding door strength testing provided by this application can significantly reduce the processing cost of the test piece, improve the accuracy and efficiency of boundary simulation, and reduce testing risks.

Description

Technical Field

[0001] This application belongs to the field of aircraft door testing, and specifically relates to a boundary simulation support device for boarding door strength testing. Background Technology

[0002] As a critical system component of an aircraft, the boarding door is subject to detailed verification and evaluation requirements regarding its structural strength and institutional reliability under relevant airworthiness regulations. Conducting ground door tests is an important verification method for confirming the airworthiness compliance of boarding doors, and the design of the boarding door test specimen and the rationality of its test support are crucial prerequisites for successful testing.

[0003] In existing technologies, strength tests for boarding gates typically use a full-size forward fuselage or a full-size aircraft as the test platform, mounting the gate on a ring-shaped fuselage structure for testing. However, using a full-size forward fuselage or the entire aircraft as a test platform increases the limitations imposed by the aircraft structure on the installation space of the test loading system, and increases the difficulty of test design and implementation. Simultaneously, simulating slight fuselage deformation under emergency landing conditions with a full-size forward fuselage or a full-size aircraft is extremely difficult, making it impossible for the boarding gate structure to meet the verification requirements of airworthiness regulations. Furthermore, using a full-size forward fuselage or a full-size aircraft as a strength test platform results in high manufacturing costs for the test components. Additionally, conducting strength tests on the boarding gate as an independent component during full-aircraft ground testing increases the overall testing cycle, raises the technical risks of full-aircraft testing, and hinders the safe and efficient progress of full-aircraft ground testing. During the design and development of the boarding gate, iterative optimization based on test results is necessary. If verification tests are only conducted after the forward fuselage design is completed or the full-aircraft testing phase, it will severely impact the boarding gate structural design and finalization process. Summary of the Invention

[0004] The purpose of this application is to provide a boundary simulation support device for boarding door strength testing, in order to solve or mitigate at least one of the problems in the prior art.

[0005] The technical solution of this application is: a boundary simulation support device for boarding door strength testing, comprising:

[0006] Experimental framework;

[0007] Boarding gate test piece;

[0008] The fuselage skin adapter assembly connects the boarding door test specimen and the boundary stiffness active control system, and is used to transfer the boundary stiffness generated by the boundary stiffness active control system to the boarding door test specimen.

[0009] An active boundary stiffness control system, installed on the test frame and connected to the fuselage skin adapter assembly, is used to generate adjustable boundary stiffness to support the boarding door test piece, thereby simulating the boundary stiffness of the boarding door.

[0010] Preferably, the boarding door test piece includes a boarding door, a fuselage frame, and a transition boundary. The boarding door and fuselage frame are used to simulate the boarding door and fuselage frame in a real aircraft structure. The transition boundary is set at the edge of the fuselage frame and is used for the stepped thickening of the fuselage skin to achieve proportional reinforcement of the stringers and ribs.

[0011] Preferably, the fuselage skin transition assembly includes a transition plate and a transition pull plate. The transition plate has a shape that fits the shape of the fuselage skin and is used to simulate the fuselage skin. One end of the transition plate is fixedly connected to the transition boundary of the boarding door test piece, and the other end is hinged to the transition pull plate. The other end of the transition pull plate is connected to the boundary stiffness active control system.

[0012] Preferably, the transition plate has a triangular structure, and one end of the transition plate has a stepped structure. Two symmetrical transition plates are laid to form a groove at one end of the stepped structure. The transition boundary is set in the groove, thereby realizing the connection between the boarding door test piece and the fuselage skin transition assembly.

[0013] The adapter plate has a single and double ear structure. The double ear end is hinged to one corner of the transition plate, and the single ear end is connected to the boundary stiffness active control system. A joint bearing is installed inside the single ear end.

[0014] Preferably, the transition plate and the fuselage skin are designed with equal strength.

[0015] Preferably, the boundary stiffness active control system includes a base plate, a rotary motor, a coupling, a lead screw, a lead screw nut, a slide rail, a slider, a spring plate, a fixed support, a movable support, a constraint support, a displacement sensor, a motor mounting base, and a lead screw mounting base.

[0016] The base plate is fixed on the test frame, the slide rail is fixed on the base plate, the slider is installed on the slide rail, the fixed support is installed at one end of the base plate, and the motor mounting base is fixed at the other end of the base plate.

[0017] The constraint support connected to the adapter plate of the fuselage skin adapter assembly is fixed on the spring plate, and one end of the spring plate is set on the fixed support and the other end is slidably installed in the movable support, while the movable support is fixed on the slider.

[0018] The rotary motor is fixed to the base plate by a motor mounting bracket, and the lead screw is connected to the rotary motor by a coupling and is also fixed to the base plate by a fixed support and a lead screw mounting bracket.

[0019] The lead screw passes through the movable support and is fitted with a lead screw nut on the movable support;

[0020] The displacement sensor is mounted on the base plate via a buffer pad and is used to measure the position of the movable support.

[0021] Preferably, the displacement sensor is a magnetostrictive displacement sensor, and the slider of the magnetostrictive displacement sensor is mounted on a movable support.

[0022] Preferably, the spring plate has multiple sets of mounting holes along its length.

[0023] Preferably, the test frame includes a bottom platform, vertical beams, horizontal beams, a top longitudinal beam, and a top horizontal beam, which are connected by connectors to form a rectangular frame structure.

[0024] The boundary simulation support device for boarding door strength testing provided in this application can significantly reduce the processing cost of test pieces, improve the accuracy and efficiency of boundary simulation for test support, and reduce test risks. Attached Figure Description

[0025] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0026] Figure 1 This is a schematic diagram of the boundary simulation support device of this application.

[0027] Figure 2 This is a schematic diagram of the boarding gate test piece for this application.

[0028] Figure 3 This is a schematic diagram of the fuselage skin adapter assembly of this application.

[0029] Figure 4 This is a schematic diagram of the active boundary stiffness control system of this application.

[0030] Figure 5 This is a schematic diagram of the experimental framework for this application.

[0031] Figure 6 This is a schematic diagram illustrating the support configuration of a boarding gate test piece according to an embodiment of this application.

[0032] Figure label:

[0033] 1-Boarding door test piece

[0034] 11-Boarding Gate

[0035] 12-Fuselage Frame

[0036] 13-Transition Boundary

[0037] 2-Fuselage skin adapter assembly

[0038] 21-Transition Plate

[0039] 22-Adapter Plate

[0040] 3-Active Boundary Stiffness Control System

[0041] 31-Base Plate

[0042] 32-Rotary Motor

[0043] 33-Coupling

[0044] 34-lead screw

[0045] 35-Screw Nut

[0046] 36-Slide Rail

[0047] 37-Slider

[0048] 38-Spring Plate

[0049] 39-Fixed Support

[0050] 310-Mobile Support

[0051] 311-Constraint Support

[0052] 312-Magnetostrictive Displacement Sensor

[0053] 313-Buffer Pad

[0054] 314-Motor Mounting Mount

[0055] 315-Screw fixing seat

[0056] 4-Experimental Framework

[0057] 41-Bottom Platform

[0058] 42-Vertical Beam

[0059] 43-Crossbeam

[0060] 44-Top longitudinal beam

[0061] 45-Top crossbeam Detailed Implementation

[0062] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0063] To address the problems of high cost, high risk, poor applicability, and poor timeliness associated with using a full-size forward fuselage or the entire aircraft as a support platform for boarding door strength testing, this application proposes a boundary simulation support device that can effectively reduce testing costs and risks while improving the efficiency of boarding door strength testing. The device in this application only requires the fabrication of the boarding door and the transition fuselage frame, and can simulate fuselage support stiffness, effectively reducing testing costs and risks.

[0064] like Figure 1 As shown, the boundary simulation support device for boarding door strength testing provided in this application includes a boarding door test piece 1, a fuselage skin transition assembly 2, a boundary stiffness active control system 3, and a test frame 4. Multiple sets of the fuselage skin transition assembly 2 and the boundary stiffness active control system 3 are provided. Each set's fuselage skin transition assembly 2 is bolted to the edge of the boarding door test piece 1, and is connected to the boundary stiffness active control system 3, which is fixed to the test frame 4. The boarding door test piece 1 is supported on the test frame 4 by the fuselage skin transition assembly 2 and the boundary stiffness active control system 3. Simultaneously, the boundary simulation stiffness of the boarding door test piece 1 by the fuselage skin transition assembly 2 is adjusted by the movement of the boundary stiffness active control system 3.

[0065] like Figure 2 The diagram shows a schematic of the boarding door test piece in this application. The boarding door test piece 1 includes a boarding door 11, a fuselage frame 12, and a transition boundary 13. In a preferred embodiment of this application, both the boarding door 11 and the fuselage frame 12 are made of real aircraft door components. Using a real fuselage frame 12 to support the boarding door 11 ensures that the load transfer between the boarding door 11 and the real fuselage frame 12 is completely consistent with the real structure during the boarding door strength test. The transition boundary 13 wraps around the edge of the fuselage frame 12 and is used for the stepped thickening of the fuselage skin, achieving proportional reinforcement of the stringers and ribs. The transition boundary 13 should be machined universally for connection with the fuselage skin transition assembly 2. By setting the transition boundary 13 on the outside of the fuselage frame 12, this application can ensure that the load of the external support is diffused through the transition boundary 13 and transmitted to the fuselage frame 12. Compared with the stiffness and strength of general fixtures, which far exceed those of the fuselage mechanism, the influence of the support system must be reduced through the diffusion of the transition section. The boarding door test piece 1 of this application only requires setting a fuselage frame 12 on the outside of the boarding door 11 and processing a corresponding number of transition boundaries 13. After being combined and installed with the boarding door 11, it can form a boarding door test piece 1 that meets the test requirements. The cost is much lower than that of the forward fuselage support, and the size of the boarding door test piece 1 is also smaller than that of the full-size forward fuselage, which reduces the requirements for the test site.

[0066] like Figure 3The diagram shows the fuselage skin transition assembly of this application. The fuselage skin transition assembly 2 includes a transition plate 21 and a transition pull plate 22. The left edge of the transition plate 21 has a stepped structure. Two transition plates 21 are symmetrically arranged, thus forming a groove 24 on the left side for connection with the boarding door test piece 1. The groove 24 clamps the transition boundary 13 of the boarding door pressure testing machine 1 and is secured with bolts. The main body of the transition plate 21 adopts a shape that conforms to the fuselage skin, simulating the fuselage skin. A circular hole is provided on its right side.

[0067] In a preferred embodiment of this application, the transition plate 21 adopts a design with the same strength as the fuselage skin, which can reduce its own weight and effectively improve the test loading accuracy. Furthermore, the transition plate 21 adopts a triangular structure, which can effectively reduce the structural weight.

[0068] The adapter plate 22 has a single and double ear structure. Its double ear end is connected to the round hole of the transition plate 21 by a pin. A joint bearing is installed in the round hole of the single ear end of the adapter plate 22, and the single ear end is connected to the boundary stiffness active control system 3 to ensure the degree of freedom of the boundary constraint.

[0069] The transition plate 21 and the transition boundary 13 are fixedly connected by bolts. At the same time, the transition plate 21 and the adapter plate 22 are connected by pins. The adapter plate 22 is equipped with a joint bearing, which can effectively release the degree of freedom of the transition plate 21 and the transition boundary 13. During the test, when the fuselage frame 12 deforms along the radial direction of the fuselage, the fuselage skin adapter assembly 2 can follow the movement to avoid the fuselage being subjected to unreasonable external forces.

[0070] The left end of the fuselage skin transition assembly 2 is connected to the boarding door test piece 1, the right end is connected to the boundary stiffness active control system 3, and the middle part (the connection point between the transition plate 21 and the transition pull plate 22) is connected to the test frame 4, thereby realizing the transformation of the surface boundary of the fuselage skin into the point boundary of the joint bearing on the transition pull plate 22.

[0071] like Figure 4 The boundary stiffness active control system 3 in this application includes a base plate 31, a rotary motor 32, a coupling 33, a lead screw 34, a lead screw nut 35, a slide rail 36, a slider 37, a spring plate 38, a fixed support 39, a movable support 310, a constraint support 311, a displacement sensor 312, a buffer pad 313, a motor mounting base 314, and a lead screw mounting base 315.

[0072] The base plate 31 is the main load-bearing component. The slide rail 36 is bolted to the base plate 31, and the slider 37 is mounted on the slide rail 36. The constraint support 311 is fixed to the spring plate 38. One end of the spring plate 38 is mounted on the fixed support 39 fixed to the base plate 31, and the other end is slidably placed in the movable support 310. At the same time, the movable support 310 is fixed to the slider 37. The lead screw 34 passes through the lower circular hole of the movable support 310, and the lead screw nut 35 passes through the lead screw 34 and is fixed to the threaded hole on the front side of the movable support 310, thereby connecting the lead screw 34 and the movable support 310 together.

[0073] The displacement sensor 312 is fixed to the base plate 31 using a buffer pad 313 and is used to measure the position of the movable support 310. In this embodiment of the application, the displacement sensor 312 is a magnetostrictive displacement sensor, and the slider of the magnetostrictive displacement sensor is fixed to the movable support.

[0074] The rotary motor 32 is fixed to the base plate 31 via the motor mounting bracket 314. The lead screw 34 is connected to the rotary motor 32 via the coupling 33 and is also fixed to the base plate 31 via the fixed support 39 and the lead screw mounting bracket 315. The base plate 31 is designed with countersunk mounting holes for connecting the base plate 31 to the test frame 4.

[0075] The boundary stiffness active control system 3 of this application is set approximately perpendicular to the boarding door test piece 1. The rotation of the rotary motor 32 drives the lead screw 34 to rotate through the coupling 33, causing the movable support 310 to move on the lead screw 34, thereby adjusting the distance between the constraint support 311, the fixed support 39, and the movable support 310, and thus adjusting the support stiffness.

[0076] This application utilizes the characteristic that the two constraint support points of the spring plate 38 have different distances and different deflection curves, and controls the support stiffness of the spring plate 38 by adjusting the distance between the two support points. Compared with conventional designs, where the stiffness adjustment of the spring plate is usually achieved by determining the position between supports that meet the stiffness requirements through multiple calibration tests, and then drilling holes on-site to fix the movable support, in the device of this application, the rotation of the rotary motor 32 drives the coupling 33 and the lead screw 34 to rotate, which in turn drives the slider 37 and the movable support 310 to move on the slide rail 36 through the lead screw nut 35. The displacement sensor 312 accurately detects the position of the movable support 310, thereby achieving active and efficient control of the position of the movable support 310 and completing the stiffness adjustment of the spring plate 38.

[0077] In a preferred embodiment of this application, multiple sets of mounting holes are provided along the length of the spring plate 38, thereby covering multiple deflection curves and increasing the applicability of the device.

[0078] like Figure 5The test frame 4 shown in this application includes a bottom platform 41, vertical beams 42, horizontal beams 43, a top longitudinal beam 44, and a top horizontal beam 45. The bottom platform 41, vertical beams 42, horizontal beams 43, top longitudinal beams 44, and top horizontal beam 45 are all bolted together to form a rectangular frame structure. The platform 41, vertical beams 42, horizontal beams 43, top longitudinal beams 44, and top horizontal beam 45 can all be used to fix the boundary stiffness active control system 3 to support the test of the boarding door test piece 1. The front of this rectangular frame is open for the installation of the boarding door test piece 1 and components such as the fuselage skin adapter assembly 2. In a preferred embodiment of this application, the test frame 4 adopts a self-balancing design, effectively reducing the requirements for the test site and improving the versatility of the device.

[0079] In a preferred embodiment of this application, the height of the bottom platform 41 of the test frame 4 from the ground is greater than the height of the anchor bolt fixing nut, which facilitates the installation of the anchor bolt when fixing the test equipment on the bottom platform 41.

[0080] like Figure 6 The diagram illustrates how four sets of fuselage skin transition assemblies 2 and an active boundary stiffness control system 3 support the boarding door test piece 1 in this embodiment of the application. The four sets of fuselage skin transition assemblies 2 are connected to the four edges (top, bottom, left, and right) of the boarding door test piece 1, respectively. The four sets of active boundary stiffness control systems 3 connect the fuselage skin transition assemblies 2 and the test frame 4, thereby fixing the boarding door test piece 1 onto the test frame 4. During testing, by controlling the active boundary stiffness control system 3 individually or collaboratively, the support stiffness of the fuselage skin transition assemblies 2 for the boarding door test piece 1 under different conditions can be simulated.

[0081] It should be noted that, depending on the shape of the cabin door and the constraint requirements, the fuselage skin transition assembly 2 and the boundary stiffness active control system 3 in this application can be used in greater quantities or in more sets to support the boarding door test piece 1.

[0082] The boundary simulation support device for boarding door strength testing provided in this application can significantly reduce the processing cost of test pieces, improve the accuracy and efficiency of boundary simulation for test support, and reduce test risks.

[0083] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A boundary simulation support device for boarding door strength testing, characterized in that, include: Experimental framework (4); The boarding door test piece (1) includes a boarding door (11), a fuselage frame (12) and a transition boundary (13). The boarding door (11) and the fuselage frame (12) adopt the boarding door and fuselage frame in the actual aircraft structure. The transition boundary (13) is set on the edge of the fuselage frame (12) for the stepped thickening of the fuselage skin to achieve proportional reinforcement of the stringers and ribs. The fuselage skin transition assembly (2) connects the boarding door test piece (1) and the boundary stiffness active control system (3) to transfer the boundary stiffness generated by the boundary stiffness active control system (3) to the boarding door test piece (1). The fuselage skin transition assembly (2) includes a transition plate (21) and a transition pull plate (22). The transition plate (21) has a shape that fits the shape of the fuselage skin and is used to simulate the fuselage skin. One end of the transition plate (21) is fixedly connected to the transition boundary (13) of the boarding door test piece (1), and the other end is hinged to the transition pull plate (22). The other end of the transition pull plate (22) is connected to the boundary stiffness active control system (3). The boundary stiffness active control system (3) is installed on the test frame (4) and connected to the fuselage skin adapter assembly (2) to generate adjustable boundary stiffness. The boundary stiffness is used to support the boarding door test piece (1) to realize the simulation support of the boarding door boundary stiffness. The boundary stiffness active control system (3) includes a base plate (31), a rotary motor (32), a coupling (33), a lead screw (34), a lead screw nut (35), a slide rail (36), a slider (37), a spring plate (38), a fixed support (39), a movable support (310), a constraint support (311), a displacement sensor (312), a motor mounting base (314), and a lead screw mounting base (315). Among them, the base plate (31) is fixed on the test frame (4), the slide rail (36) is fixed on the base plate (31), the slider (37) is installed on the slide rail (36), the fixed support (39) is installed on one end of the base plate (31), and the motor mounting bracket (314) is fixed on the other end of the base plate (31); the constraint support (311) connected to the adapter plate (22) of the fuselage skin adapter assembly (2) is fixed on the spring plate (38), and one end of the spring plate (38) is set on the fixed support (39), and the other end is slidably installed in the movable support (310). At the same time, the movable support (310) The rotary motor (32) is fixed on the base plate (31) via the motor mounting bracket (314). The lead screw (34) is connected to the rotary motor (32) via the coupling (33) and is also fixed on the base plate (31) via the fixed support (39) and the lead screw mounting bracket (315). The lead screw (34) passes through the movable support (310) and is fitted with the lead screw nut (35) on the movable support (310). The displacement sensor (312) is mounted on the base plate (31) via the buffer pad (313) and is used to measure the position of the movable support (310).

2. The boundary simulation support device for boarding door strength testing as described in claim 1, characterized in that, The transition plate (21) is a triangular structure, and one end of the transition plate (21) is provided with a stepped structure. Two symmetrical transition plates (21) are laid to form a groove at one end of the stepped structure. The transition boundary (13) is set in the groove, thereby realizing the connection between the boarding door test piece (1) and the fuselage skin transition assembly (2). The adapter plate (22) has a single and double ear structure. The double ear end is hinged to one corner of the transition plate (21), and the single ear end is hinged to the boundary stiffness active control system (3). A joint bearing is provided inside the single ear end.

3. The boundary simulation support device for boarding door strength testing as described in claim 2, characterized in that, The transition plate (21) and the fuselage skin are designed with equal strength.

4. The boundary simulation support device for boarding door strength testing as described in claim 1, characterized in that, The displacement sensor (312) is a magnetostrictive displacement sensor, and the slider of the magnetostrictive displacement sensor is mounted on the movable support (310).

5. The boundary simulation support device for boarding door strength testing as described in claim 1, characterized in that, The spring plate (38) has multiple sets of mounting holes along its length.

6. The boundary simulation support device for boarding door strength testing as described in claim 1, characterized in that, The test frame (4) includes a bottom platform (41), vertical beams (42), horizontal beams (43), top longitudinal beams (44) and top horizontal beams (45). The bottom platform (41), vertical beams (42), horizontal beams (43), top longitudinal beams (44) and top horizontal beams (45) are connected by connectors to form a rectangular frame structure.

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