Flight deck assembly and manned aerial vehicle

Abstract

The utility model provides a flight frame assembly and manned aircraft relates to manned aircraft technical field. Flight frame assembly includes frame structure and skin assembly, skin assembly includes first skin and second skin, first skin is connected with frame structure in one side in first direction, second skin is connected with frame structure in the other side in first direction, when flight frame assembly is in use state, first direction is parallel with gravity direction, this makes first skin and second skin locate frame structure's upper and lower two sides respectively. First skin and second skin are all integrated components, namely first skin is integrated, second skin is also integrated, first skin and second skin do not need to manufacture part respectively after splicing, has simplified manufacturing technology to improve the manufacturing efficiency of first skin and second skin.

Description

Technical Field

[0001] This application relates to the field of manned aircraft technology, and in particular to a flight frame assembly and a manned aircraft. Background Technology

[0002] In manned aircraft, the skin refers to the structure covering the exterior of the aircraft's frame structure. It is the primary load-bearing structure that withstands air resistance during flight. The skin includes the upper skin and lower skin, among others. All parts of the skin structure are made of carbon fiber. The upper and lower skins cover the upper and lower surfaces of the frame structure, respectively, and are the two largest parts in terms of area. Currently, the upper and lower skins are generally manufactured by producing multiple separate parts and then assembling them together.

[0003] However, the manufacturing processes for the upper and lower skins are relatively complex, and the production efficiency of the upper and lower skins is low. Utility Model Content

[0004] In view of this, this application provides a flight frame assembly and a manned aircraft to address, to some extent, the problem of low production efficiency of the upper and lower skins.

[0005] According to one aspect of this application, a flight frame assembly is provided, the flight frame assembly including a frame structure and a skin assembly, the skin assembly including a first skin and a second skin, the first skin being connected to one side of the frame structure in a first direction, and the second skin being connected to the other side of the frame structure in the first direction, wherein when the flight frame assembly is in use, the first direction is parallel to the direction of gravity;

[0006] Both the first skin and the second skin are integrally molded parts.

[0007] Preferably, both the first skin and the second skin are made of aluminum alloy.

[0008] Preferably, the first skin can be connected to the cabin, and the first skin is a 2-series aluminum alloy component.

[0009] Preferably, the second skin is a 7-series aluminum alloy component.

[0010] Preferably, at least one of the first skin and the second skin has an access port, and the skin assembly further includes a cover and fasteners, the cover being detachably mounted on the access port by the fasteners.

[0011] Preferably, there are multiple fasteners arranged around the edge of the cover, and the distance between two adjacent fasteners is equal to 8 times the diameter of the fastener.

[0012] Preferably, the cover is made of 2-series aluminum alloy.

[0013] Preferably, the skin assembly further includes a first fairing and a second fairing, the first fairing and the second fairing being connected to opposite sides of the frame structure in a second direction, the second direction intersecting the first direction.

[0014] Preferably, the frame structure includes two mounting components and multiple ribs, the two mounting components are arranged at intervals along a third direction, and the third direction intersects the plane determined by the first direction and the second direction;

[0015] The plurality of said ribs are arranged at intervals along the second direction, and for any one of said ribs, both said mounting components are connected to said rib;

[0016] Each of the mounting components is connected to the first skin and the second skin on both sides in the second direction, and each of the ribs is connected to the first skin and the second skin on both sides in the second direction.

[0017] Preferably, the first and second air deflectors are fixed to two of the plurality of ribs located at the edges.

[0018] According to another aspect of this application, a manned aircraft is provided, the manned aircraft including the flight frame assembly described above.

[0019] The flight frame assembly of this application includes a frame structure and a skin assembly. The skin assembly includes a first skin and a second skin. The first skin is connected to one side of the frame structure in a first direction, and the second skin is connected to the other side of the frame structure in the first direction. When the flight frame assembly is in use, the first direction is parallel to the direction of gravity, which places the first skin and the second skin on the upper and lower sides of the frame structure, respectively. Both the first skin and the second skin are integrally molded parts; that is, the first skin is integrally molded, and the second skin is also integrally molded. The first skin and the second skin do not need to be manufactured separately and then spliced, simplifying the manufacturing process and thus improving the manufacturing efficiency of the first skin and the second skin. Attached Figure Description

[0020] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 A schematic diagram of the flight frame assembly is shown.

[0022] Figure 2 An exploded view of the flight frame assembly is shown;

[0023] Figure 3 A structural diagram of the frame structure is shown;

[0024] Figure 4 A schematic diagram of the structure of a manned spacecraft is shown.

[0025] Icons: 1-Frame structure; 11-Mounting components; 111-First beam; 112-Second beam; 113-Fixing frame; 12-Rib plate; 13-First support; 14-Second support; 2-First skin; 3-Second skin; 4-Cover; 5-Inspection port; 6-First fairing; 7-Second fairing; 81-Mounting beam; 82-Fixing component; 83-Stabilizing component; 84-Mounting frame; 85-Shell; 91-Nacelle; 92-Arm arm; L1-First direction; L2-Second direction; L3-Third direction. Detailed Implementation

[0026] The following detailed embodiments are provided to help the reader gain a comprehensive understanding of the methods, apparatus, and / or systems described herein. However, various changes, modifications, and equivalents of the methods, apparatus, and / or systems described herein will be apparent after understanding the disclosure of this application. For example, the order of operations described herein is merely illustrative and is not limited to the order set forth herein; changes that will be apparent after understanding the disclosure of this application are possible, except for operations that must occur in a specific order. Furthermore, for clarity and brevity, descriptions of features known in the art may be omitted.

[0027] The features described herein may be implemented in different forms and should not be construed as being limited to the examples described herein. Rather, the examples described herein have been provided merely to illustrate some of the many feasible ways of implementing the methods, apparatus, and / or systems described herein that will be apparent upon understanding the disclosure of this application.

[0028] Throughout the specification, when an element (such as a layer, region, or substrate) is described as being "on" another element, "connected to" another element, "bonded to" another element, "on" another element, or "covering" another element, it may be directly "on" another element, "connected to" another element, "bonded to" another element, "on" another element, or "covering" another element, or there may be one or more other elements in between. In contrast, when an element is described as being "directly on" another element, "directly connected to" another element, "directly bonded to" another element, "directly on" another element, or "directly covering" another element, there may be no other elements in between.

[0029] As used herein, the term “and / or” includes any one of the relevant items listed and any combination of any two or more items.

[0030] Although terms such as “first,” “second,” and “third” may be used herein to describe individual components, assemblies, regions, layers, or parts, these components, assemblies, regions, layers, or parts are not limited by these terms. Rather, these terms are used only to distinguish one component, assembly, region, layer, or part from another. Therefore, without departing from the teachings of the examples described herein, the first component, assembly, region, layer, or part referred to as the second component, assembly, region, layer, or part may also be referred to as the second component, assembly, region, layer, or part.

[0031] For ease of description, spatial relation terms such as “above,” “upper,” “below,” and “lower” are used herein to describe the relationship between one element and another, as shown in the accompanying drawings. Such spatial relation terms are intended to include not only the orientation depicted in the drawings but also different orientations of the device during use or operation. For example, if the device in the drawings is flipped, an element described as being “above” or “upper” relative to another element will subsequently be “below” or “lower” relative to that other element. Therefore, the term “above” includes both “above” and “below” orientations depending on the spatial orientation of the device. The device may also be positioned in other ways (e.g., rotated 90 degrees or in other orientations), and the spatial relation terms used herein will be interpreted accordingly.

[0032] The terminology used herein is for the purpose of describing various examples only and is not intended to limit this disclosure. Unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. The terms “comprising,” “including,” and “having” enumerate the stated features, quantities, operations, components, elements, and / or combinations thereof, but do not exclude the presence or addition of one or more other features, quantities, operations, components, elements, and / or combinations thereof.

[0033] Variations in the shapes shown in the accompanying drawings may occur due to manufacturing techniques and / or tolerances. Therefore, the examples described herein are not limited to the specific shapes shown in the accompanying drawings, but include changes in shape that may occur during manufacturing.

[0034] The features of the examples described herein can be combined in various ways that will be apparent upon understanding the disclosure of this application. Furthermore, although the examples described herein have a wide variety of constructions, other constructions are possible, as will be apparent upon understanding the disclosure of this application.

[0035] The following will combine Figures 1 to 4 The application describes the flight frame assembly and the manned aircraft. Figures 1 to 4 In the middle, the first direction L1 intersects with the second direction L2, and the third direction L3 intersects with the plane determined by the first direction L1 and the second direction L2, wherein the intersection is preferably perpendicular. The flight frame component and manned aircraft of this application will be described below in combination with the case that the first direction L1, the second direction L2 and the third direction L3 are perpendicular to each other.

[0036] According to one aspect of this application, a flight frame assembly is provided, such as... Figures 1 to 3 As shown, the flight frame assembly includes a frame structure 1 and a skin assembly. The skin assembly includes a first skin 2 and a second skin 3. The first skin 2 is connected to one side of the frame structure 1 in a first direction L1, and the second skin 3 is connected to the other side of the frame structure 1 in the first direction L1. When the flight frame assembly is in use, the first direction L1 is parallel to the direction of gravity, which places the first skin 2 and the second skin 3 on the upper and lower sides of the frame structure 1, respectively. Both the first skin 2 and the second skin 3 are integrally molded parts. Since the first skin 2 and the second skin 3 are integrally molded, they do not need to be manufactured separately and then spliced, simplifying the manufacturing process and thus improving the manufacturing efficiency of the first skin 2 and the second skin 3.

[0037] Furthermore, both the first skin 2 and the second skin 3 are made of aluminum alloy, which is cheaper and reduces the manufacturing cost of the first skin 2 and the second skin 3. In addition, the use of aluminum alloy for the first skin 2 and the second skin 3 meets the requirement of integral molding of the first skin 2 and the second skin 3.

[0038] like Figure 1 and Figure 2 As shown, the skin assembly also includes a first fairing 6 and a second fairing 7, which are respectively connected to the two opposite sides of the frame structure 1 in the second direction L2, so that the first fairing 6 and the second fairing 7 cover the two sides of the frame structure 1 in the second direction L2.

[0039] Optionally, the first fairing 6 and the second fairing 7 can be made of 2-series aluminum alloy, and the first fairing 6 and the second fairing 7 can be formed by cold stamping.

[0040] In the embodiments of this application, such as Figure 2 and Figure 3 As shown, the frame structure 1 includes two mounting components 11 and multiple ribs 12. The two mounting components 11 are arranged at intervals along a third direction L3, and the multiple ribs 12 are arranged at intervals along a second direction L2. For any rib 12, both mounting components 11 are connected to the rib 12.

[0041] Optionally, the number of ribs 12 can be four, six, eight, or more. Preferably, the number of ribs 12 is six, and the frame structure 1 will be described below with reference to the number of ribs 12 being six.

[0042] like Figure 3 As shown, the frame structure 1 includes a first beam 111, a second beam 112, and two fixed frames 113. The two second beams 112 are located between the two first beams 111. The middle portion of the first beam 111 protrudes towards the second beam 112 relative to its two ends. The middle portion of the second beam 112 protrudes away from the first beam 111 relative to its two ends. The ends of the first beam 111 and the second beam 112 on the same side in the second direction L2 are connected to the same fixed frame 113. The ends of the first beam 111 and the second beam 112 on the other side in the second direction L2 are connected to another fixed frame 113. For the two ribs 12 located at the edges, the two ends of the ribs 12 in the third direction L3 are connected to the two second beams 112 respectively. For the four ribs 12 located in the middle, the two ends of the ribs 12 in the third direction L3 are connected to the two first beams 111 respectively, and the two second beams 112 are connected to the middle portion of the ribs 12. The first rib 12 near the edge is connected to the adjacent fixed frame 113 by a first support 13, and the rib 12 and the adjacent rib 12 are connected by a second support 14.

[0043] Optionally, the aforementioned rib plate 12 and the first beam 111, rib plate 12 and the second beam 112, the first beam 111 and the fixing frame 113, rib plate 12 and the first support member 13, the first support member 13 and the fixing frame 113, the second support member 14 and the rib plate 12, and the second beam 112 and the fixing frame 113 can all be fixed by rivets, and the fixing frame 113 is used to fix the arm 92.

[0044] like Figure 2 As shown, the flight frame assembly also includes a mounting beam 81. Mounting frames 84 for fixing the arms 92 are fixed to both ends of the mounting beam 81. Two fasteners 82 are fixed to the mounting beam 81, spaced apart along a third direction L3. The two fasteners 82 are connected by two stabilizers 83. Rivets pass through the fasteners 82, the first skin 2, and the rib 12 to secure the fasteners 82. Rivets also pass through the stabilizers 83, the second beam 112, and the rib 12 to stabilize the stabilizers 83. Thus, the mounting beam 81 is fixed using the stabilizers 83 and the fasteners 82. A cover 85 can be installed on one of the stabilizers 83.

[0045] In the embodiments of this application, the shapes of the first skin 2 and the second skin 3 are adapted to the shape of the frame structure 1. The two ends of the first beam 111 in the second direction L2 are exposed outside the first skin 2 and the second skin 3, and the two ends of the second beam 112 in the second direction L2 are exposed outside the first skin 2 and the second skin 3, thereby exposing the fixing frame 113 outside the first skin 2 and the second skin 3. The first beam 111 is exposed outside the first skin 2 and the second skin 3 on the side of the third direction L3 opposite to the second beam 112. The four ribs 12 located in the middle are located between the first skin 2 and the second skin 3, and the ribs 12 located at the edges are respectively arranged close to the edges of the first skin 2 and the second skin 3 in the second direction L2. The first guide 6 and the second guide 7 are respectively connected to the two edge ribs 12.

[0046] Optionally, the first skin 2, the second skin 3, the first fairing 6, and the second fairing 7 described above can be connected to different parts of the frame structure 1 by rivets.

[0047] Furthermore, the first skin 2 is also used to connect with the nacelle 91. The first skin 2 is made of 2-series aluminum alloy, which gives it good fatigue resistance and allows it to adapt to positional fluctuations in the nacelle 91. Optionally, the first skin 2 can be formed by a bending process.

[0048] Preferably, the second skin 3 is made of 7-series aluminum alloy, which gives the second skin 3 high structural strength, meeting the structural strength requirements of the flight frame assembly. Optionally, the second skin 3 can be formed by a thermoforming process.

[0049] In embodiments of this application, at least one of the first skin 2 and the second skin 3 is provided with an access port 5, and the skin assembly further includes a cover 4 and fasteners. Figures 1 to 3 (Not shown in the image) The cover 4 is detachably attached to the access port 5 by fasteners. When the flight frame assembly is being inspected, the fasteners can be removed, at which point the cover 4 can be separated from the first skin 2 or the second skin 3, exposing the access port 5 for inspection work.

[0050] Optionally, the number of inspection ports 5 on the first skin 2 and the second skin 3 can be selected according to requirements, for example, such as Figure 2 As shown, a maintenance opening 5 is provided on the first skin 2, and a cover 4 is provided on the maintenance opening 5. Four maintenance openings 5 ​​are provided on the second skin 3. The four maintenance openings 5 ​​are arranged at intervals along the second direction L2. One of the maintenance openings 5 ​​is covered by a cover 4, and the other three maintenance openings 5 ​​are covered by the same cover 4.

[0051] Preferably, the cover 4 can be made of 2-series aluminum alloy, which gives the cover 4 good fatigue resistance and can meet the needs of disassembling the cover 4 multiple times during routine inspection and maintenance of electrical equipment. The cover 4 can be formed by cold stamping process.

[0052] Furthermore, each cover 4 is secured by multiple fasteners, which are arranged around the edge of the cover 4. The distance between two adjacent fasteners is equal to eight times the diameter of the fastener. This reduces the number of fasteners while meeting the need to secure the cover 4, thereby reducing the cost of the flight frame assembly.

[0053] Preferably, the fastener is a screw, in which case tightening the fastener will allow the cover 4 to be installed and removed.

[0054] Furthermore, the various parts of the skin assembly in this application are aluminum alloy parts formed by hot forming, cold stamping, and bending, which have short processing times and are conducive to mass production. At the same time, aluminum alloy has a lower cost, which can reduce the cost of the skin assembly.

[0055] According to another aspect of this application, a manned aircraft is provided, such as... Figure 4 As shown, the manned aircraft includes the aforementioned flight frame assembly, which has the same technical effects as the aforementioned flight frame assembly, and will not be described again here.

[0056] In addition, the manned aircraft also includes a cabin 91, which is fixed to the flight frame assembly.

[0057] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this utility model, and are not intended to limit it. Although the utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this utility model.

Claims

1. A flight frame assembly, characterized in that, The flight frame assembly includes a frame structure and a skin assembly. The skin assembly includes a first skin and a second skin. The first skin is connected to one side of the frame structure in a first direction, and the second skin is connected to the other side of the frame structure in the first direction. When the flight frame assembly is in use, the first direction is parallel to the direction of gravity. Both the first skin and the second skin are integrally molded parts.

2. The flight frame assembly according to claim 1, characterized in that, Both the first skin and the second skin are made of aluminum alloy.

3. The flight frame assembly according to claim 2, characterized in that, The first skin can be connected to the cabin, and the first skin is a 2-series aluminum alloy component.

4. The flight frame assembly according to claim 3, characterized in that, The second skin is made of 7-series aluminum alloy.

5. The flight frame assembly according to claim 1, characterized in that, At least one of the first skin and the second skin has an access port, and the skin assembly also includes a cover and fasteners, the cover being detachably attached to the access port by the fasteners.

6. The flight frame assembly according to claim 5, characterized in that, The number of fasteners is multiple, and the multiple fasteners are arranged around the edge of the cover. The distance between two adjacent fasteners is equal to 8 times the diameter of the fastener.

7. The flight frame assembly according to claim 5, characterized in that, The cover is made of 2-series aluminum alloy.

8. The flight frame assembly according to any one of claims 1-7, characterized in that, The skin assembly further includes a first fairing and a second fairing, the first fairing and the second fairing being connected to opposite sides of the frame structure in a second direction, the second direction intersecting the first direction.

9. The flight frame assembly according to claim 8, characterized in that, The frame structure includes two mounting components and multiple ribs. The two mounting components are arranged at intervals along a third direction, which intersects the plane defined by the first direction and the second direction. The plurality of said ribs are arranged at intervals along the second direction, and for any one of said ribs, both said mounting components are connected to said rib; Each of the mounting components is connected to the first skin and the second skin on both sides in the second direction, and each of the ribs is connected to the first skin and the second skin on both sides in the second direction.

10. The flight frame assembly according to claim 9, characterized in that, The first and second air deflectors are respectively fixed to two of the multiple ribs located at the edges.

11. A manned aircraft, characterized in that, The manned aircraft includes the flight frame assembly as described in any one of claims 1-10.

Images