Aircraft windshield window frame framework assembly

Abstract

An aircraft windshield window frame framework assembly, comprising: window frame frameworks (20), which comprise main windshield opening frames (21) surrounding main windshields (11) of an aircraft and side windshield opening frames (22) surrounding side windshields (12) of the aircraft, wherein the main windshield opening frames (21) and the side windshield opening frames (22) are mounted on and fitted with the corresponding main windshields (11) and side windshields (12) by means of tight fit to form an integral whole, the two main windshield opening frames (21) are in direct contact and are connected in a butt joint manner, and each main windshield opening frame (21) and the corresponding side windshield opening frame (22) are in direct contact and are connected in a butt joint manner. The design of butt-joint connection of the opening frames of the four integral window frame frameworks and the use of connecting belt plates at butt-joint sections of the opening frames make a force transfer route of the window frame frameworks at connection sections more direct, thereby achieving higher load transfer efficiency and structural use efficiency, and reducing the manufacturing difficulty and manufacturing cost on the premise of meeting the load-bearing design requirement.

Description

Aircraft windshield frame assembly Technical Field

[0001] The present invention relates to an aircraft windshield window frame assembly, specifically, to a window frame assembly for a load-bearing windshield and the structure for directly connecting the window frame frames to each other. The present invention relates to the design of an integral window frame for a load-bearing aircraft windshield, and pertains to the field of aircraft windshield window frame frame design and connection methods. Background Art

[0002] The aircraft windshield window frame assembly (also known as the windshield skylight frame assembly) is located in the canopy area of ​​the aircraft nose, directly in front of the pilot. It is the most critical structural component in the entire canopy area and the first part positioned during assembly of the entire upper nose. Comprehensive consideration must be given to the window frame's connection method, shape control, and manufacturability during the manufacturing process.

[0003] In the existing technology, the mainstream aircraft windshields and their window frame frames are mainly the following:

[0004] 1. For A320 series aircraft, the windshield is a flat plate type, and the corresponding window frame is a flat form. The ventilation window and the rear side window are separated by a closed frame. The frames of the windshield and side windows are connected to the other frames and wall panels through joints.

[0005] 2. The B737-700 aircraft features a flat, bolted windshield. The corresponding window frame is flat, with adjacent window frames aligned sequentially. The entire structure is die-forged, with flanges at the front and bottom of the die-forged component connecting to the fuselage frame and fuselage stringers. The flanges extend from the die-forged component and connect to the corresponding fuselage stringers and fuselage frame via joints.

[0006] 3. For the ERJ-190 aircraft, the main windshield is a curved surface, and the corresponding window frame skeleton is a segmented combination form. A central column is required, and joints are required to connect with the fuselage frame and fuselage long stringers.

[0007] However, the windshields used in existing aircraft models rarely participate in overall fuselage force transmission. To ensure the canopy area meets bird strike mitigation requirements and the pressure differential loads required during normal flight, the window frame itself requires high strength and rigidity. The window frame requires a central column and is relatively thick and heavy overall.

[0008] In addition, due to the need for structural strength, the window frame skeletons selected for the models in service are all segmented combinations connected to each other, rather than integral window frames. They have many structural components, complex and diverse connection forms, are difficult to manufacture, and assembly accuracy is difficult to guarantee.

[0009] At present, more advanced aircraft under development, such as the C919, have begun to adopt large-area double-curvature load-bearing windshields. The windshields can withstand and transmit a certain load at the nose of the aircraft, so the load-bearing capacity requirements for the window frame skeleton are correspondingly reduced.

[0010] Therefore, there is a need for a window frame that is lighter and easier to manufacture corresponding to the load-bearing windshield design.

[0011] Summary of the Invention

[0012] In response to the above-mentioned problems of the prior art, the purpose of the present invention is to provide an aircraft windshield window frame skeleton assembly to meet the window frame skeleton requirements corresponding to the load-bearing windshield design, reduce the manufacturing difficulty and manufacturing cost of the window frame while meeting the load-bearing requirements, and increase its processing and assembly positioning accuracy.

[0013] To address the aforementioned issues, the present invention provides an aircraft windshield window frame assembly based on a load-bearing windshield. In a first example of the aircraft windshield window frame assembly, the aircraft windshield window frame assembly includes a window frame, the window frame frame including a main windshield frame surrounding the aircraft's main windshield and a side windshield frame surrounding the aircraft's side windshields. The main windshield frame and the side windshield frame are tightly fitted and integrally assembled with the corresponding main windshield and side windshield, wherein the two main windshield frames are in direct contact and abutting connection, and the main windshield frame and the side windshield frame are in direct contact and abutting connection.

[0014] In a second example of the aircraft windshield window frame assembly, optionally including the first example, the main windshield window frame is a single-piece, integral window frame, and the side windshield window frames are single-piece, integral window frames.

[0015] In a third example of the aircraft windshield window frame skeleton assembly, which optionally includes one or more of the first and second examples, two main windshield opening frames are in direct contact and connected to form an "I" shape.

[0016] In a fourth example of the aircraft windshield window frame skeleton assembly, one or more of the first to third examples may be optionally included, wherein the main windshield frame is in a "Z" shape, and the side windshield frame is in a "Γ" shape, and the corresponding main windshield frame is in direct contact with and abutted against the corresponding side windshield frame, and the abutted main windshield frame and the side windshield frame are further formed by adding flanges on the basis of the "Z" shape. Font.

[0017] In the fifth example of the aircraft windshield window frame skeleton assembly, one or more of the first to fourth examples may be optionally included, and at the position where the two main windshield opening frames are in direct contact and abutted connection, and at the position where the corresponding main windshield opening frame is in direct contact and abutted connection with the side windshield opening frame, the aircraft windshield window frame skeleton assembly further includes a window frame connecting strip, which is installed at the docking interface of the corresponding left and right main windshield opening frames, or installed at the docking interface of the corresponding main windshield opening frame and the side windshield opening frame, and the load-bearing windshield is connected to the corresponding window frame skeleton by fasteners and the fasteners pass through the window frame connecting strip, connecting the load-bearing windshield, the window frame connecting strip and the window frame skeleton into a whole.

[0018] In the sixth example of the aircraft windshield window frame skeleton assembly, one or more of the first to fifth examples may be optionally included, and the main windshield opening frame and the side windshield opening frames in the window frame skeleton are connected to the fuselage frame and the fuselage long stringers through edge strips extending from the window frame skeleton.

[0019] In the seventh example of the aircraft windshield window frame skeleton assembly, one or more of the first to sixth examples may be optionally included, and reinforcement members are used to connect the edge strips extending from the window frame skeleton to the fuselage frame and the fuselage stringers.

[0020] The design of the integral aircraft windshield window frame skeleton assembly of the present invention adopts a design of direct butt-jointed connection of the window frames at the original central column and side column positions, thereby reducing the overall thickness of the window frame. It extends upward and downward at the original columns, directly butting or overlapping with the surrounding structure, eliminating the need for connection joints. The butt-jointed connection design of the mouth frames of the four integral window frame skeletons and the use of connecting strips at the butt sections of the mouth frames allow the force transmission route of the window frame skeleton at the connection sections to be changed directly, achieving higher load transmission efficiency and higher structural utilization efficiency. On the premise of meeting the load-bearing design requirements, the simple cross-sectional form of the window frame greatly reduces the manufacturing difficulty and manufacturing cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to describe embodiments in which the above and other features of the present invention may be obtained, a more particular description of the invention briefly described above will be presented with reference to exemplary embodiments of the invention illustrated in the accompanying drawings. It will be understood that these drawings depict only exemplary embodiments of the invention and are not to be considered limiting of its scope, and the invention will be described and explained with additional specificity and detail through the use of the accompanying drawings. In the drawings:

[0022] 1 is a front cross-sectional perspective view of a position where two integral main windshield opening frames of an aircraft windshield window frame assembly are connected according to a preferred embodiment of the present invention;

[0023] 2 is a front cross-sectional perspective view of a position where a main windshield frame and a side windshield frame of an aircraft windshield window frame skeleton assembly are connected in conjunction with each other according to a preferred embodiment of the present invention;

[0024] FIG3 is a perspective schematic diagram of the connection between the window frame skeleton, the fuselage stringer and the fuselage frame according to a preferred embodiment of the present invention.

[0025] Figures 1 to 3 are roughly drawn to scale, however, the dimensions in the drawings are only schematic and not necessarily drawn to scale, but are intended to provide a clearer illustration. In other embodiments, other relative dimensions may be used.

[0026] Here and throughout the following, identical features appearing in different figures are denoted by identical or similar reference numerals.

[0027] Reference numerals list: 10 load-bearing windshield 11 main windshield 12 side windshield 20 window frame 21 main windshield opening frame 22 side windshield opening frame 23 window frame connecting strip DETAILED DESCRIPTION

[0028] The present invention will be further described below with reference to specific embodiments and accompanying drawings. More details are set forth in the following description to facilitate a full understanding of the present invention. However, the present invention can obviously be implemented in a variety of other ways different from the description herein. Those skilled in the art can make similar generalizations and deductions based on actual application situations without violating the connotation of the present invention. Therefore, the scope of protection of the present invention should not be limited by the content of this specific embodiment.

[0029] 1 schematically shows a front cross-sectional perspective view of a preferred embodiment of an aircraft windshield window frame assembly at a location where two main windshield opening frames are connected.

[0030] The window frame skeleton 20 may include two main windshield opening frames 21 correspondingly surrounding the main windshield 11 and two side windshield opening frames 22 correspondingly surrounding the side windshields 12 .

[0031] In the preferred embodiment, both the main windshield frame 21 and the side windshield frames 22 are integral, reducing manufacturing costs. Due to the use of a load-bearing windshield, the load-bearing requirements for the window frame skeleton of the present invention are correspondingly reduced. The window frame skeleton 20 utilizes a design consisting of four integral window frames. This ensures that the curved surface of the window frame skeleton 20 and the load-bearing windshield 10 are integrated, creating a high degree of conformity with the windshield's integral pressure plate, meeting the requirements for a smooth appearance and effectively preventing air leakage.

[0032] In Figure 1, two main windshield opening frames 21 are directly connected to form an "I" shape. Preferably, due to the use of a load-bearing windshield, the load-bearing requirements for the window frame of the present invention are correspondingly reduced. Therefore, this "I" beam can serve as the central column of the load-bearing windshield, eliminating the need for a heavy single-piece central column.

[0033] Turning now to FIG. 2 , FIG. 2 schematically shows a front cross-sectional perspective view of a position where a main windshield frame and a side windshield frame of an aircraft windshield window frame skeleton assembly according to a preferred embodiment of the present invention are connected.

[0034] In FIG2 , the main windshield frame 21 is in a “Z” shape, and the side windshield frame 22 is in a “Γ” shape.

[0035] The left or right main windshield frame 21 is directly in contact with the corresponding side windshield frame 22 and is connected to each other, and a flange is added on the basis of the "Z" shape to further form a The above-mentioned “I” beam can be used as the side column of the load-bearing windshield, and The letter beam can improve the overall bending resistance, while leaving enough open space for the cutting tools used in manufacturing, greatly reducing the manufacturing difficulty.

[0036] As can be seen from Figures 1 and 2, window frame connecting strips 23 are also included at the positions where the two main windshield frames 21 are directly connected, and at the positions where the corresponding main windshield frame 21 is directly connected to the side windshield frame 22. The window frame connecting strips 23 can be fixedly attached to the corresponding main windshield frame 21, or can be fixedly attached to the corresponding main windshield frame 21 and the side windshield frame 22.

[0037] The load-bearing windshield 10 is mounted to the window frame 20 using known connectors. In a preferred embodiment, one end of these connectors is connected to the load-bearing windshield 10, and the other end can be connected to the window frame connecting strip 23 and the window frame 20. The addition of the window frame connecting strip 23 to the window frame 20 is intended to provide a more direct load transfer path at the central pillar and side pillars, thereby improving the overall load transfer efficiency of the structure.

[0038] Turning now to FIG. 3 , FIG. 3 schematically shows a perspective view of the connection between the window frame skeleton, the fuselage stringer and the fuselage frame according to a preferred embodiment of the present invention.

[0039] The main windshield frame 21 and the side windshield frames 22 of the window frame frame 20 are connected to the fuselage frame and fuselage stringers via flanges extending from the window frame frame 20. Advantageously, due to the use of a load-bearing windshield, the load-bearing requirements of the window frame frame of the present invention are correspondingly reduced. Therefore, reinforcements can be used to connect the flanges extending from the window frame frame 20 to the fuselage frame and fuselage stringers, while still meeting the load-bearing requirements at the nose of the aircraft, without the need for joints. Consequently, the number of parts required for connection is reduced, and processing and assembly are simplified.

[0040] The aircraft windshield window frame skeleton assembly according to the present invention reduces the overall thickness of the window frame by adopting a design in which the window frame frames are directly connected to each other at the positions of the original central column and side columns.

[0041] Extending upward and downward from the original columns, the system directly connects or overlaps the surrounding structure, eliminating the need for joints. The structural cross-section formed by the integral window frame at the column face joint incorporates an external window frame connecting plate, making the load transfer path more direct and improving the overall structural load transfer efficiency.

[0042] The window frame matching design and the use of connecting strips make it possible to directly change the force transmission route at the connecting sections of each frame of the window frame skeleton, thereby achieving higher structural efficiency, a wider driving field of view, a better aerodynamic shape and better workability. At the same time, it reduces manufacturing costs while meeting the load-bearing requirements and still meets the load-bearing capacity required during assembly.

[0043] In order to make the objectives, technical solutions and advantages of the embodiments of the present invention more clear, the technical solutions of the present invention are clearly and completely described above in conjunction with the specific embodiments of the present invention and the accompanying drawings.

[0044] Although various embodiments have been described above, it should be understood that the embodiments described are only some of the embodiments of the present invention, rather than all of the embodiments, and are presented in an exemplary rather than restrictive manner. It will be apparent to those skilled in the relevant art that the disclosed subject matter can be implemented in other specific forms without departing from its spirit and essential characteristics.

[0045] Therefore, the above-described embodiments are considered to be illustrative and non-restrictive in all aspects, and are not to be used as a basis for limiting the present invention in any way.

[0046] Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without inventive effort are within the scope of protection of the present invention. The present disclosure also includes various modifications and variations within the scope of equivalence. In addition, various combinations and methods, as well as other combinations and methods including only one element, more than one element, or less than one element, are also within the scope and scope of the present disclosure.

Claims

1. An aircraft windshield window frame skeleton assembly, characterized in that: The aircraft windshield window frame skeleton assembly comprises: A window frame skeleton (20), the window frame skeleton (20) comprising a main windshield frame (21) surrounding a main windshield (11) of an aircraft and a side windshield frame (22) surrounding a side windshield (12) of the aircraft, wherein the main windshield frame (21) and the side windshield frame (22) are installed and matched with the corresponding main windshield (11) and the side windshield (12) in a tight fit to form an integral body, The two main windshield opening frames (21) are directly in contact and connected in abutment with each other, and The main windshield frame (21) and the side windshield frame (22) are in direct contact and are in abutment connection.

2. The aircraft windshield window frame skeleton assembly according to claim 1, characterized in that: The main windshield frame (21) is a single-piece integral frame, and The side windshield frame (22) is a single-piece integral frame.

3. The aircraft windshield window frame skeleton assembly according to claim 1, characterized in that: The two main windshield opening frames (21) are in direct contact and are joined together to form an "I" shape.

4. The aircraft windshield window frame skeleton assembly according to claim 1, characterized in that: The main windshield frame (21) is in a "Z" shape, and the side windshield frame (22) is in a "Γ" shape. The corresponding main windshield frame (21) and the corresponding side windshield frame (22) are in direct contact and are connected in abutment with each other. The main windshield frame (21) and the side windshield frame (22) are connected to each other by adding flanges on the basis of the "Z" shape to further form Font.

5. The aircraft windshield window frame skeleton assembly according to claim 1, characterized in that: At the position where the two main windshield frames (21) are directly in contact and connected, and at At the position where the corresponding main windshield frame (21) and the side windshield frame (22) are directly in contact and abuttingly connected, the aircraft windshield window frame skeleton assembly further comprises a window frame connecting strip plate (23), the window frame connecting strip plate (23) being installed at the corresponding butt joint interface of the left and right main windshield frames (21), or installed at the corresponding butt joint interface of the main windshield frame (21) and the side windshield frame (22), and The load-bearing windshield (10) is connected to the corresponding window frame frame (20) via fasteners, and the fasteners pass through the window frame connecting strip (23), thereby connecting the load-bearing windshield (10), the window frame connecting strip (23) and the window frame frame (20) into a whole.

6. The aircraft windshield window frame skeleton assembly according to claim 1, characterized in that: The main windshield frame (21) and the side windshield frame (22) in the window frame skeleton (20) are connected to the fuselage frame and the fuselage long stringer via edge strips extending from the window frame skeleton (20).

7. The aircraft windshield window frame skeleton assembly according to claim 6, characterized in that: The edge strip extending from the window frame skeleton (20) is connected to the fuselage frame and the fuselage long stringer by using a reinforcement member.

Images