Airplane windshield structure ground strength test platform

Abstract

The invention belongs to the field of airplane structure ground strength tests, and particularly relates to an airplane windshield structure ground strength test platform. Comprising a plurality of supporting stand columns which are fixedly mounted on a bearing terrace; the sealing bottom plate is provided with a fixing fake piece positioning groove, a supporting stand column connecting hole, a wire outlet hole, an air inflation / deflation hole, a fixing fake piece connecting hole, a lifting hole and a measurement feedback hole. A fixing false piece of the windshield structure test piece is arranged in the fixing false piece positioning groove and is fixedly connected with the sealing bottom plate through the fixing false piece connecting hole; and the force load applying lever system is connected with the fixing false piece and is used for applying boundary force load to the windshield structure test piece. The device is suitable for airplane strength tests, especially static strength tests, damage safety tests and fatigue tests of the airplane windshield structure, can apply equivalent air pressure loads and boundary force loads to the airplane windshield structure, and can truly simulate the stress condition of the airplane windshield structure during high-altitude service.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of aircraft structure ground strength test, and particularly relates to an aircraft windshield structure ground strength test platform. BACKGROUND

[0002] The aircraft windshield structure includes windshield glass and its connecting parts. As an important component on the aircraft, the windshield structure bears structural boundary force load and cabin internal and external pressure difference load. In recent years, aircraft cockpit windshield structure damage events occur from time to time. For example, for Boeing 787, CRJ900, B737-800 and Airbus A320-200, windshield structure damage occurs in different situations during service, causing great economic loss and serious threat to personnel safety. Therefore, the aircraft windshield structure needs to be subjected to relevant static strength test, damage safety test and fatigue strength test to show that it meets the airworthiness regulation requirements, meets the national military standard requirements and meets the strength design requirements.

[0003] At present, the aircraft windshield structure test cannot truly simulate the stress condition of the aircraft windshield structure in high-altitude service due to the difficulty in reproducing the multi-field coupling load of the high-altitude environment, resulting in a significant difference between the test results and the real failure mode (such as micro-crack propagation and seal aging).

[0004] Therefore, there is an urgent need for a technical solution to overcome or alleviate at least one of the above-mentioned defects of the prior art. SUMMARY

[0005] The purpose of the present application is to provide an aircraft windshield structure ground strength test platform to solve at least one problem existing in the prior art.

[0006] The technical solution of the present application is:

[0007] An aircraft windshield structure ground strength test platform, comprising:

[0008] Supporting columns, comprising a plurality of supporting columns, the plurality of supporting columns are fixedly installed on a force-bearing terrace;

[0009] A sealing bottom plate, the sealing bottom plate is provided with a fixed dummy part positioning groove, a supporting column connecting hole, a wire outlet hole, a gas charging / discharging hole, a fixed dummy part connecting hole, a hoisting hole and a measurement feedback hole, wherein,

[0010] The supporting column connecting hole is used to fix and install the sealing bottom plate on the supporting column;

[0011] The wire outlet hole is used to lead the cable out of the cabin;

[0012] The gas charging / discharging hole is connected with the gas charging station through a gas charging pipeline and is used to provide gas pressure load to the cabin;

[0013] The lifting hole is used for lifting the sealing bottom plate;

[0014] The measurement feedback hole is used for connecting a measuring instrument with a control system;

[0015] The fixed dummy of the wind deflector structure test piece is arranged in the fixed dummy positioning groove and fixedly connected with the fixed dummy connecting hole of the sealing bottom plate through a connecting piece;

[0016] The force load applying lever system is connected with the fixed dummy and used for applying a boundary force load to the wind deflector structure test piece.

[0017] In at least one embodiment of the present application, the support column comprises a horizontal beam, a vertical beam and a first diagonal brace, wherein,

[0018] The bottom connecting hole for connecting with the force bearing terrace is arranged on the horizontal beam;

[0019] The vertical beam is welded with the horizontal beam, and a connecting plate is arranged on the vertical beam, and the top connecting hole for connecting with the sealing bottom plate is arranged on the connecting plate;

[0020] The two ends of the first diagonal brace are welded with the horizontal beam and the vertical beam respectively.

[0021] In at least one embodiment of the present application, the support column further comprises a second diagonal brace, and the two ends of the second diagonal brace are welded with two adjacent horizontal beams respectively.

[0022] In at least one embodiment of the present application, the measurement feedback hole comprises an air pressure sensor feedback hole and a pressure gauge feedback hole.

[0023] In at least one embodiment of the present application, after the fixed dummy of the wind deflector structure test piece is arranged in the fixed dummy positioning groove and fixedly connected with the fixed dummy connecting hole of the sealing bottom plate through the connecting piece, a sealing treatment is performed by using a rubber strip.

[0024] In at least one embodiment of the present application, the force load applying lever system comprises a double lug joint, a connecting pull plate and a lever, wherein,

[0025] The double lug joint is connected with the fixed dummy;

[0026] One end of the connecting pull plate is connected with the double lug joint, and the other end is connected with the lever.

[0027] In at least one embodiment of the present application, a single lug joint is arranged at one end of the connecting pull plate connected with the lever.

[0028] The invention has at least the following beneficial technical effects:

[0029] The aircraft windshield structure ground strength test platform of the present application is suitable for aircraft strength test, in particular aircraft windshield structure static strength test, damage safety test and fatigue test, can apply equivalent air pressure load and boundary force load to the aircraft windshield structure, and can truly simulate the stress condition of the aircraft windshield structure in high altitude service. BRIEF DESCRIPTION OF DRAWINGS

[0030] Figure 1 is a schematic diagram of the aircraft windshield structure ground strength test platform of an embodiment of the present application as a whole;

[0031] Figure 2 is a schematic diagram of the support column of the aircraft windshield structure ground strength test platform of an embodiment of the present application;

[0032] Figure 3 is a schematic diagram of the sealing bottom plate of the aircraft windshield structure ground strength test platform of an embodiment of the present application;

[0033] Figure 4 is a schematic diagram of the force load applying lever system of the aircraft windshield structure ground strength test platform of an embodiment of the present application.

[0034] Among them:

[0035] 1-support column, 11-horizontal beam, 12-vertical beam, 13-first diagonal brace, 14-second diagonal brace, 15-bottom connecting hole, 16-connecting plate, 17-top connecting hole;

[0036] 2-sealing bottom plate, 21-fixed dummy part positioning groove, 22-support column connecting hole, 23-wiring hole, 24-charging / discharging hole, 25-fixed dummy part connecting hole, 26-lifting hole, 27-measurement feedback hole;

[0037] 3-windshield structure test piece;

[0038] 4-force load applying lever system, 41-double lug joint, 42-connecting pull plate, 43-lever;

[0039] 5-force bearing terrace. DETAILED DESCRIPTION

[0040] For the purpose, technical solutions and advantages of the embodiments of the present application, the technical solutions of the embodiments of the present application will be described in more detail below in combination with the drawings in the embodiments of the present application. In the drawings, the same or similar notations represent the same or similar elements or elements with the same or similar functions throughout. The described embodiments are part of the embodiments of the present application, not all embodiments. The embodiments described below by reference to the drawings are exemplary and are intended to explain the present application, and cannot be understood as limiting the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative labor fall within the scope of protection of the present application. The embodiments of the present application will be described in detail below in combination with the drawings.

[0041] In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the scope of protection of the present application.

[0042] The embodiments of the present application will be described in detail below in combination with the drawings. Figures 1 to 4 The present application will be described in further detail.

[0043] The present application provides an aircraft windshield structure ground strength test platform, as shown in FIG. 1, comprising: support columns 1, a sealed floor 2, a windshield structure test piece 3, and a force load applying lever system 4. Figure 1

[0044] Specifically, the support column 1 comprises a plurality of support columns 1 fixedly installed on the load-bearing terrace 5. As shown in FIG. 2, the support column 1 comprises a plurality of support columns 1 fixedly installed on the load-bearing terrace 5. Figure 2 ​As shown, the support column 1 is composed of several independent columns, and the heights of all the independent columns are consistent. Each independent column at least includes a horizontal beam 11, a vertical beam 12 and a first inclined brace 13. The horizontal beam 11 is provided with a bottom connecting hole 15 for connecting with the load-bearing floor 5. The horizontal beam 11 is fixedly installed on the load-bearing floor 5 through the bottom connecting hole 15 matched with a bolt. The vertical beam 12 is welded on the upper surface of the horizontal beam 11. The upper surface of the vertical beam 12 of each independent column is welded with a connecting plate 16. The connecting plate 16 is provided with a top connecting hole 17 for connecting with the sealing bottom plate 2. The vertical beam 12 is mainly used for supporting and bearing vertical load. Meanwhile, the two ends of the first inclined brace 13 are welded with the horizontal beam 11 and the vertical beam 12 respectively. The first inclined brace 13 is used for bearing lateral load in the direction. In the embodiment, three horizontal beams 11 are arranged in parallel. One vertical beam 12 is arranged on each of the horizontal beams 11 at the two sides. Two vertical beams 12 are arranged on the horizontal beam 11 in the middle. Each vertical beam 12 is connected with the corresponding horizontal beam 11 through the first inclined brace 13. In addition, the two vertical beams 12 on the horizontal beam 11 in the middle are further connected through a connecting beam, so as to improve the stability of the whole support column 1.

[0045] In the preferred embodiment of the present application, the support column 1 further includes a second inclined brace 14. The two ends of the second inclined brace 14 are welded with the horizontal beams 11 of two adjacent independent columns respectively. The second inclined brace 14 is used for bearing lateral load in another direction.

[0046] As shown in the figure, Figure 3 The sealing bottom plate 2 is provided with a fixed false part positioning groove 21, a support column connecting hole 22, a wire outlet hole 23, a charging / discharging hole 24, a fixed false part connecting hole 25, a lifting hole 26 and a measurement feedback hole 27. The sealing bottom plate 2 is fixedly installed on the support column 1 through the support column connecting hole 22 matched with the top connecting hole 17. The wire outlet hole 23 is used for leading the cable out of the cabin. The cable includes an in-cabin strain cable, a sensor cable and the like. The charging / discharging hole 24 is connected with a charging station through a charging pipeline, and is used for providing air pressure load to the cabin. The lifting hole 26 is used for lifting the sealing bottom plate 2. The lifting of the whole sealing bottom plate 2, the installation and the movement are realized through the lifting hole 26 matched with a lifting device. The measurement feedback hole 27 is used for connecting a measuring instrument with a control system, so as to realize the collection and control of the parameters in the cabin. The fixed false part positioning groove 21 and the fixed false part connecting hole 25 are used for installing the fixed false part of the windscreen structure test piece 3.

[0047] In the preferred embodiment of the present application, the measurement feedback hole 27 includes an air pressure sensor feedback hole for connecting the air pressure sensor with the control system, and a pressure gauge feedback hole for connecting the precision pressure gauge and contact pressure gauge with the control system, so that the control system can read the values of the air pressure sensor, precision pressure gauge and contact pressure gauge connected to the feedback holes to form a closed-loop control and realize real-time observation of the cabin pressure.

[0048] As shown in Figure 4 The fixed dummy of the windscreen structure test piece 3 is arranged in the fixed dummy positioning groove 21 and fixedly connected with the fixed dummy connecting hole 25 of the sealing bottom plate 2 through the connecting piece. The windscreen structure test piece 3 and the fixed dummy can be provided by the test entrusting party.

[0049] In the preferred embodiment of the present application, the lower hole position of the fixed dummy of the windscreen structure test piece 3 is connected with the fixed dummy connecting hole 25 of the sealing bottom plate 2 to form an internal cavity, and the cavity is inflated to apply the air pressure load. The connection is sealed by using a rubber strip.

[0050] As shown in Figure 4 The force load applying lever system 4 is connected with the fixed dummy and used for applying boundary force load to the windscreen structure test piece 3. The force load applying lever system 4 includes a double lug joint 41, a connecting pull plate 42 and a lever 43. The double lug joint 41 is connected with the upper surface hole position of the fixed dummy. One end of the connecting pull plate 42 is threadedly or boltedly connected with the double lug joint 41, and the other end is connected with the lever 43. The connecting pull plate 42 is provided with a single lug joint at the end connected with the lever 43. After the load synthesis by the force load applying lever system 4, the force load applying lever system 4 is connected with the load applying devices such as the force sensor and the actuator to apply the boundary force load to the windscreen structure test piece 3.

[0051] The aircraft windscreen structure ground strength test platform of the present application supports the support column 1 fixed to the load-bearing terrace 5 by the anchor bolt to support and constrain the whole platform. The sealing bottom plate 2 and the fixed dummy of the windscreen structure test piece 3 form a closed cavity. The sealing bottom plate 2 is provided with the charging / discharging hole 24, various connecting holes and feedback holes for connection with the fixed dummy and application of the air pressure load to the windscreen structure test piece 3. The force load applying lever system 4 is connected with the fixed dummy and used for applying the boundary force load to the windscreen structure test piece 3. The present application can be used to simulate the air pressure load and the boundary force load borne by the aircraft windscreen structure in service, and is suitable for the static strength test, damage safety test and fatigue test of the aircraft windscreen structure.

[0052] The above merely provides the specific implementation of the present application, but the protection scope of the present application is not limited to this. Any person skilled in the art can easily think of the changes or replacements within the technical range disclosed by the present application, which should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. An aircraft windshield ground strength test platform, characterized by, The utility model relates to a wind -resistant structure test piece test device, including: Supporting column (1) including a plurality of, a plurality of supporting column (1) fixed mounting on force floor (5); Sealing bottom plate (2), the sealing bottom plate (2) is set up with fixed false part positioning groove (21), supporting column connecting hole (22), outgoing line hole (23), charge / discharge hole (24), fixed false part connecting hole (25), hoist hole (26) and measurement feedback hole (27) including, wherein, Supporting column connecting hole (22) is used for fixing and mounting sealing bottom plate (2) on supporting column (1); Outgoing line hole (23) is used for leading cable from cabin; Charge / discharge hole (24) is connected with charge station through inflation pipeline and is used for providing air pressure load to cabin; Hoist hole (26) is used for hoisting sealing bottom plate (2); Measurement feedback hole (27) is used for connecting measuring instrument with control system; Wind -resistant structure test piece (3), the fixed false part of wind -resistant structure test piece (3) is arranged in fixed false part positioning groove (21), and is fixedly connected with fixed false part connecting hole (25) of sealing bottom plate (2) through connecting piece; Force load applying lever system (4) is connected with the fixed false part, and is used for applying boundary force load to wind -resistant structure test piece (3).

2. The aircraft windshield structure ground strength test platform of Claim 1, wherein, Supporting column (1) includes horizontal beam (11), vertical beam (12) and first inclined brace (13), wherein, Horizontal beam (11) is set up with bottom connecting hole (15) for connecting with force floor (5); Vertical beam (12) is welded with horizontal beam (11), and connecting plate (16) is installed on vertical beam (12), and top connecting hole (17) for connecting with sealing bottom plate (2) is set up on connecting plate (16); Two ends of first inclined brace (13) are welded with horizontal beam (11) and vertical beam (12) respectively.

3. The aircraft windshield structure ground strength test platform of Claim 2, wherein, Supporting column (1) further includes second inclined brace (14), and two ends of second inclined brace (14) are welded with two adjacent horizontal beams (11) respectively.

4. The aircraft windshield ground strength test platform of Claim 1, wherein, Measurement feedback hole (27) includes air pressure sensor feedback hole and pressure gauge feedback hole.

5. The aircraft windshield ground strength test platform of Claim 1, wherein, The fixed false part of wind -resistant structure test piece (3) is arranged in fixed false part positioning groove (21), and is fixedly connected with fixed false part connecting hole (25) of sealing bottom plate (2) through connecting piece, and is sealed by adhesive tape after being handled.

6. The aircraft windshield ground strength test platform of Claim 1, wherein, Force load applying lever system (4) includes double lug joint (41), connecting pull plate (42) and lever (43), wherein, Double lug joint (41) is connected with fixed false part; One end of connecting pull plate (42) is connected with double lug joint (41), and the other end is connected with lever (43).

7. The aircraft windshield ground strength test platform of Claim 6, wherein, The end of connecting pull plate (42) connected with lever (43) is provided with single lug joint.

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