Manned vehicle frame and manned vehicle

Abstract

The utility model provides a kind of manned aircraft frame and manned aircraft, it is related to manned aircraft technical field.Manned aircraft frame includes two installation components and multiple rib plates, installation component includes first beam, second beam and two first installation frames, the both ends of first beam are connected with two first installation frames respectively, the both ends of second beam are connected with two first installation frames respectively, the middle part of first beam is protruding towards second beam to opposite ends, the middle part of second beam is protruding to the direction of away from first beam to opposite ends, two installation components are arranged along first direction interval, two second beams are located between two first beams;Multiple rib plates are arranged along second direction interval, for any rib plate, at least one of first beam and second beam in each installation component is connected with rib plate, when manned aircraft arm is loaded in vehicle, the space formed in the side of first beam back to second beam after arm bending.

Description

Technical Field

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

[0002] A manned aircraft typically consists of a frame, a cabin, and multiple arms, all of which are fixed to the frame. The cabin is fixed to the bottom of the frame. The frame is the main load-bearing component of a manned aircraft, serving to support and transfer loads.

[0003] When a manned aircraft is not in flight, it needs to be placed inside a vehicle. However, the aircraft occupies a large space and poses a significant risk of interference with other structures within the vehicle. Utility Model Content

[0004] In view of this, this application provides a manned aircraft frame and a manned aircraft to solve the problems of the large space occupied by the manned aircraft and the high risk of interference with other structures inside the vehicle.

[0005] According to one aspect of this application, a manned aircraft frame is provided, the manned aircraft frame including two mounting components and a plurality of ribs, the mounting components including a first beam, a second beam and two first mounting frames, the two ends of the first beam being connected to the two first mounting frames respectively, the two ends of the second beam being connected to the two first mounting frames respectively, the middle portion of the first beam protruding toward the second beam relative to the two ends of the first beam, the middle portion of the second beam protruding away from the first beam relative to the two ends of the second beam, the two mounting components being arranged at intervals along a first direction, and the two second beams being located between the two first beams;

[0006] The plurality of ribs are arranged at intervals along a second direction, which intersects the first direction. For any rib, at least one of the first beam and the second beam in each mounting assembly is connected to the rib.

[0007] Preferably, the number of ribs is an even number greater than or equal to four, and the plurality of ribs are divided into a first connecting group and a second connecting group, wherein the first connecting group includes two ribs;

[0008] The rib in the first connecting group is connected to two second beams at both ends in the first direction. The second connecting group is located between the two ribs in the first connecting group. For any rib in the second connecting group, the two first beams and the two second beams in the two mounting assemblies are connected to the rib.

[0009] Preferably, the mounting assembly further includes a first support member, the two ends of which are connected to two adjacent ribs near the edge of the second connection group.

[0010] Preferably, the mounting assembly further includes a second support member, one end of which is connected to the first rib near the edge of the second connection group, and the other end of which is connected to the first mounting frame. The first support member and the second support member are connected to the same rib.

[0011] Preferably, the mounting components and the plurality of ribs are all aluminum alloy parts.

[0012] Preferably, the second beam has a plurality of first wire harness through holes, which are arranged at intervals and penetrate the second beam.

[0013] Preferably, each of the ribs in the second connection group is provided with a second wire harness through hole, the second wire harness through hole penetrating the rib.

[0014] Preferably, the first beam includes a first reinforcing member, a second reinforcing member, and a connecting member. The two ends of the connecting member in the second direction are respectively connected to the first reinforcing member and the second reinforcing member. The middle part of the connecting member protrudes towards the second beam relative to the two ends of the connecting member. The first reinforcing member is connected to one of the first mounting frames, and the second reinforcing member is connected to another of the first mounting frames.

[0015] Preferably, the second beam includes a connecting truss, a third reinforcing member, and a fourth reinforcing member, which are connected sequentially. The connecting truss extends along the second direction. The end of the third reinforcing member away from the connecting truss is inclined toward the first reinforcing member and is connected to the same first mounting frame as the first reinforcing member. The end of the fourth reinforcing member away from the connecting truss is inclined toward the second reinforcing member and is connected to another first mounting frame as the second reinforcing member.

[0016] Preferably, the manned aircraft frame further includes a support component and two fixing members, the two fixing members being connected to the two mounting components respectively, both fixing members being connected to the support component, the support component being located on the same side of the two mounting components in a third direction, the third direction intersecting the plane defined by the first direction and the second direction.

[0017] Preferably, the manned aircraft frame further includes two stabilizers, each stabilizer having its two ends connected to one of the two fixing members, and the two stabilizers being fixed to the two ribs respectively.

[0018] According to another aspect of this application, a manned aircraft is provided, the manned aircraft comprising the aforementioned manned aircraft frame.

[0019] The manned aircraft frame of this application includes two mounting components and multiple ribs. Each mounting component includes a first beam, a second beam, and two first mounting frames. The two ends of the first beam are connected to the two first mounting frames, and the two ends of the second beam are also connected to the two first mounting frames. The middle portion of the first beam protrudes towards the second beam relative to its two ends, while the middle portion of the second beam protrudes away from the first beam relative to its two ends. The two mounting components are spaced apart along a first direction, with the two second beams located between the two first beams. Multiple ribs are spaced apart along a second direction. For any rib, at least one of the first beam and the second beam in each mounting component is connected to the rib. Because the middle portion of the first beam protrudes towards the second beam relative to its two ends, and the middle portion of the second beam protrudes away from the first beam relative to its two ends, a space is formed on the side of the first beam facing away from the second beam that can accommodate an arm. When the manned aircraft arm is mounted inside the vehicle, the arm, after bending, resides within the space formed on the side of the first beam facing away from the second beam. In this way, the space occupied by the manned aircraft is reduced, thereby reducing the risk of structural interference between the manned aircraft and the vehicle interior. 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 This diagram shows the structural schematic of the manned spacecraft frame.

[0022] Figure 2 An exploded view of the two mounting components and the ribs is shown;

[0023] Figure 3 An exploded view showing a portion of the frame structure of a manned spacecraft;

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

[0025] Icons: 1-Mounting component; 11-First beam; 111-First reinforcing member; 112-Second reinforcing member; 113-Connector; 12-Second beam; 121-Connecting truss; 122-Third reinforcing member; 123-Fourth reinforcing member; 124-First wiring harness through hole; 13-First mounting frame; 131-Mounting component; 14-First support component; 15-Second support component; 2-Rib plate; 21-Second wiring harness through hole; 3-Supporting component; 31-Supporting body; 32-Second mounting frame; 4-Fixing component; 5-Stabilizing component; 6-Nacelle; 7-Skin; 8-Arc-shaped component; 9-Archive; 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 4The manned aircraft frame and manned aircraft of this application are described, wherein 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. The intersection is preferably perpendicular. The manned aircraft frame and manned aircraft 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 manned aircraft frame is provided, such as... Figures 1 to 3 As shown, the manned spacecraft frame includes two mounting components 1 and multiple ribs 2. The mounting components 1 include a first beam 11, a second beam 12, and two first mounting frames 13. The two ends of the first beam 11 are connected to the two first mounting frames 13 respectively, and the two ends of the second beam 12 are connected to the two first mounting frames 13 respectively. The middle part of the first beam 11 protrudes towards the second beam 12 relative to the two ends of the first beam 11, and the middle part of the second beam 12 protrudes away from the first beam 11 relative to the two ends of the second beam 12. The two mounting components 1 are arranged at intervals along a first direction L1, and the two second beams 12 are located between the two first beams 11. The multiple ribs 2 are arranged at intervals along a second direction L2. For any rib 2, at least one of the first beam 11 and the second beam 12 in each mounting component 1 is connected to the rib 2. The mounting components 1 and the multiple ribs 2 are all aluminum alloy parts. Because the middle portion of the first beam 11 protrudes towards the second beam 12 relative to its two ends, and the middle portion of the second beam 12 protrudes away from the first beam 11 relative to its two ends, a space is formed on the side of the first beam 11 facing away from the second beam 12 that can accommodate the boom 9. When the boom of the manned aircraft is mounted inside the vehicle, the boom 9, after being bent, is located within the space formed on the side of the first beam 11 facing away from the second beam 12. In this way, the space occupied by the entire manned aircraft is reduced, thereby reducing the risk of structural interference between the manned aircraft and the vehicle.

[0037] Furthermore, both the mounting components 1 and the multiple ribs 2 are made of aluminum alloy, which is cheaper than carbon fiber composites, thus reducing the manufacturing cost of the manned spacecraft frame. Simultaneously, the combination of the two mounting components 1 and the multiple ribs 2 ensures that the manned spacecraft frame possesses sufficient structural strength to meet the requirements for support and torque transmission.

[0038] Furthermore, the two mounting components 1 and the multiple ribs 2 are arranged in the above manner, such that the two mounting components 1 and the multiple ribs 2 are arranged in an "X" shape, and the load can be transferred along the two first beams 11 and the two second beams 12 to meet the load transfer requirements of the manned aircraft frame.

[0039] Optionally, such as Figure 2As shown, the first mounting frame 13 may include two mounting parts 131, which can be connected by multiple rivets. The entire first mounting frame 13 has a cuboid-like structure and is used to fix the boom 9, which includes the propeller blades.

[0040] Optionally, the number of ribs 2 is an even number greater than or equal to four, for example, the number of ribs 2 can be four, six, eight or more.

[0041] In the embodiments of this application, multiple ribs 2 are divided into a first connecting group and a second connecting group. The first connecting group includes two ribs 2. The two ends of the ribs 2 in the first connecting group are respectively connected to two second beams 12 in the first direction L1. The second connecting group is located between the two ribs 2 in the first connecting group. For any rib 2 in the second connecting group, the two first beams 11 and the two second beams 12 in the two mounting components 1 are connected to the rib 2. In this way, the connection between the two mounting components 1 and the first beams 11 and second beams 12 in the mounting components 1 is realized through the ribs 2 in the first connecting group and the second connecting group, so that the manned spacecraft frame has sufficient structural strength.

[0042] like Figure 2 As shown, the first beam 11 includes a first reinforcing member 111, a second reinforcing member 112, and a connecting member 113. The two ends of the connecting member 113 in the second direction L2 are respectively connected to the first reinforcing member 111 and the second reinforcing member 112. The middle part of the connecting member 113 protrudes towards the second beam 12 relative to the two ends of the connecting member 113. The first reinforcing member 111 and the second reinforcing member 112 are also arranged at an angle. The first reinforcing member 111 is connected to a first mounting frame 13, and the second reinforcing member 112 is connected to another first mounting frame 13.

[0043] Optionally, the cross-sections of the first reinforcing member 111 and the second reinforcing member 112 are both “└┘” shaped to facilitate the connection between the first reinforcing member 111 and the second reinforcing member 112 and the first mounting frame 13.

[0044] Furthermore, the second beam 12 includes a connecting truss 121, a third reinforcing member 122, and a fourth reinforcing member 123. The third reinforcing member 122, the connecting truss 121, and the fourth reinforcing member 123 are connected sequentially. The connecting truss 121 extends along the second direction L2. The end of the third reinforcing member 122 away from the connecting truss 121 is inclined toward the first reinforcing member 111 and is connected to the same first mounting frame 13 as the first reinforcing member 111. The end of the fourth reinforcing member 123 away from the connecting truss 121 is inclined toward the second reinforcing member 112 and is connected to another first mounting frame 13 as the second reinforcing member 112.

[0045] Optionally, the cross-sections of the third reinforcing member 122 and the fourth reinforcing member 123 are both "└┘" shaped. The first reinforcing member 111 and the third reinforcing member 122 are spliced ​​to form a cuboid space. One of the first mounting frames 13 is disposed within the cuboid space formed by the splicing of the first reinforcing members 111 and the third reinforcing member 122. The first reinforcing members 111 and the third reinforcing member 122 can be connected to the first mounting frame 13 by multiple rivets. The second reinforcing member 112 and the fourth reinforcing member 123 are spliced ​​to form a cuboid space. Another first mounting frame 13 is disposed within the cuboid space formed by the splicing of the second reinforcing members 112 and the fourth reinforcing member 123. The second reinforcing member 112 and the fourth reinforcing member 123 can be connected to the other first mounting frame 13 by multiple rivets.

[0046] Taking a number of ribs 2 as an example, the first connecting group includes two ribs 2, and the second connecting group includes four ribs 2. For the ribs 2 in the first connecting group, both ends of the ribs 2 are connected to two arc-shaped pieces 8 by rivets. The two arc-shaped pieces 8 at both ends of the first rib 2 are fixed to two third reinforcing pieces 122 by rivets, and the two arc-shaped pieces 8 at both ends of the second rib 2 are fixed to two fourth reinforcing pieces 123 by rivets.

[0047] For the rib 2 in the second connecting group, the first reinforcing member 111 and the connecting member 113 in the first mounting assembly 1 are fixed to the end of the first rib 2 by rivets, the third reinforcing member 122 and the connecting truss 121 in the first mounting assembly 1 are fixed to the same mounting position on the first rib 2 by rivets, the third reinforcing member 122 and the connecting truss 121 in the second mounting assembly 1 are fixed to the same mounting position on the first rib 2 by rivets, and the first reinforcing member 111 and the connecting member 113 in the second mounting assembly 1 are fixed to the other end of the first rib 2 by rivets. The connector 113 and the second reinforcing member 112 in the first mounting assembly 1 are fixed to the end of the fourth rib 2 by rivets. The connecting truss 121 and the fourth reinforcing member 123 in the first mounting assembly 1 are fixed to the same mounting position on the fourth rib 2 by rivets. The connecting truss 121 and the fourth reinforcing member 123 in the second mounting assembly 1 are fixed to the same mounting position on the fourth rib 2 by rivets. The connector 113 and the second reinforcing member 112 in the second mounting assembly 1 are fixed to the other end of the fourth rib 2 by rivets. The two ends of the second rib 2 are connected to the two connectors 113 by rivets. The second rib 2 has two notches at the positions corresponding to the two connecting trusses 121. The two connecting trusses 121 are located in the two notches respectively and are connected to the second rib 2 by rivets. The two ends of the third rib 2 are connected to the two connecting pieces 113 by rivets. The third rib 2 has two notches at the positions corresponding to the two connecting trusses 121. The two connecting trusses 121 are located in the two notches respectively. The two connecting trusses 121 are connected to the third rib 2 by rivets.

[0048] In the embodiments of this application, such as Figure 1 As shown, the mounting assembly 1 also includes a first support member 14, the two ends of which are connected to two adjacent ribs 2 near the edge in the second connecting group. By setting the first support member 14, the structural strength of the mounting assembly 1 can be improved, thereby improving the structural strength of the entire manned spacecraft frame.

[0049] Furthermore, the mounting assembly 1 also includes a second support member 15, one end of which is connected to the first rib 2 near the edge in the second connecting group, and the other end of which is connected to the first mounting frame 13. The first support member 14 and the second support member 15 are connected to the same rib 2, which can further improve the structural strength of the mounting assembly 1.

[0050] Optionally, the first support member 14 and the second support member 15 described above can be fixed by rivets.

[0051] In addition, the first support member 14 and the second support member 15 can also be used to fix the skin 7, thereby improving the stability of the skin 7 fixation.

[0052] Optionally, the second beam 12 has multiple first wiring harness through holes 124, which are spaced apart and pass through the second beam 12, allowing wiring harnesses to pass through. During the use of the manned aircraft frame, the frame is covered by the skin 7, and gas may enter the interior of the frame through the location of the first mounting frame 13. Because the second beam 12 has multiple first wiring harness through holes 124, gas can flow through these holes to the other first mounting frame 13, thus preventing water vapor and rainwater from accumulating inside the frame. Optionally, both the third reinforcing member 122 and the fourth reinforcing member 123 have first wiring harness through holes 124.

[0053] Furthermore, each rib 2 in the second connecting group is provided with a second wiring harness through hole 21, which penetrates the rib 2 and allows the wiring harness to pass through. The first wiring harness through hole 124 and the second wiring harness through hole 21 cooperate to allow gas entering the manned spacecraft frame to flow to another first mounting frame 13 through different paths.

[0054] In the embodiments of this application, such as Figure 1 and Figure 3 As shown, the manned spacecraft frame also includes a support assembly 3 and two fixing members 4. The support assembly 3 includes a support body 31 and two second mounting frames 32. The support body 31 is cuboid in shape. The two second mounting frames 32 are fixed to both ends of the support body 31 in the first direction L1. The two fixing members 4 are respectively fixed to the two mounting assemblies 1. Both fixing members 4 are connected to the support assembly 3. The support assembly 3 is located on the same side of the two mounting assemblies 1 in the third direction L3. In this way, the support assembly 3 is fixed by the two fixing members 4.

[0055] Optionally, the fastener 4 can be V-shaped, with an insertion opening at the tip of the fastener 4. The part supporting the main body 31 is located in the insertion opening and is fixed to the fastener 4 by rivets.

[0056] In addition, the manned spacecraft frame also includes two stabilizing components 5, each of which is connected at both ends to two fixing components 4. The two stabilizing components 5 are respectively fixed to two rib plates 2. In this way, the stabilizing components 5 achieve fixation between the two fixing components 4, and the connection between the stabilizing components 5 and the rib plates 2 can further improve the stability of the support assembly 3.

[0057] In addition, the entire outer surface of the manned aircraft frame has an anti-corrosion coating to reduce the risk of rust and corrosion, thus improving flight safety. Optionally, the anti-corrosion coating can be formed by applying anti-rust paint, electroplating, or other methods.

[0058] According to another aspect of this application, a manned aircraft is provided, the manned aircraft including the aforementioned manned aircraft frame.

[0059] Furthermore, the manned aircraft also includes a skin 7 and a cabin 6. The skin 7 covers the manned aircraft frame to protect the manned flight frame, and the cabin 6 is fixed to the bottom of the manned aircraft frame.

[0060] In addition, each of the first mounting frames 13 and the second mounting frames 32 of the manned aircraft frame is equipped with an arm 9, and the entire manned aircraft has six arms 9 with propellers, enabling the manned aircraft to fly.

[0061] When a manned aircraft is in flight, such as Figure 4 As shown, all six arms 9 extend relative to the frame of the manned aircraft. When the manned aircraft is loaded inside the vehicle, the three arms 9 on the same side in the first direction L1 are bent and placed in the space outside the first beam 11, reducing the space occupied by the entire manned aircraft and thus reducing the risk of structural interference between the manned aircraft and the vehicle.

[0062] 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 frame for a manned aircraft, characterized in that, The manned aircraft frame includes two mounting components and multiple ribs. Each mounting component includes a first beam, a second beam, and two first mounting frames. The two ends of the first beam are respectively connected to the two first mounting frames, and the two ends of the second beam are respectively connected to the two first mounting frames. The middle portion of the first beam protrudes towards the second beam relative to the two ends of the first beam, and the middle portion of the second beam protrudes away from the first beam relative to the two ends of the second beam. The two mounting components are arranged at intervals along a first direction, and the two second beams are located between the two first beams. The plurality of ribs are arranged at intervals along a second direction, which intersects the first direction. For any rib, at least one of the first beam and the second beam in each mounting assembly is connected to the rib.

2. The manned aircraft frame according to claim 1, characterized in that, The number of ribs is an even number greater than or equal to four, and the plurality of ribs are divided into a first connecting group and a second connecting group, wherein the first connecting group includes two ribs. The rib in the first connecting group is connected to two second beams at both ends in the first direction. The second connecting group is located between the two ribs in the first connecting group. For any rib in the second connecting group, the two first beams and the two second beams in the two mounting assemblies are connected to the rib.

3. The manned aircraft frame according to claim 2, characterized in that, The mounting assembly further includes a first support member, the two ends of which are connected to two adjacent ribs near the edge of the second connection group.

4. The manned aircraft frame according to claim 3, characterized in that, The mounting assembly further includes a second support member, one end of which is connected to the first rib near the edge of the second connection group, and the other end of which is connected to the first mounting frame. The first support member and the second support member are connected to the same rib.

5. The manned aircraft frame according to any one of claims 2-4, characterized in that, The mounting components and the plurality of ribs are all made of aluminum alloy.

6. The manned aircraft frame according to any one of claims 2-4, characterized in that, The second beam has multiple first wire harness through holes, which are arranged at intervals and penetrate the second beam.

7. The manned aircraft frame according to claim 6, characterized in that, Each of the ribs in the second connection group is provided with a second wire harness through hole, which penetrates the rib.

8. The manned aircraft frame according to any one of claims 2-4, characterized in that, The first beam includes a first reinforcing member, a second reinforcing member, and a connecting member. The two ends of the connecting member in the second direction are respectively connected to the first reinforcing member and the second reinforcing member. The middle part of the connecting member protrudes towards the second beam relative to the two ends of the connecting member. The first reinforcing member is connected to one of the first mounting frames, and the second reinforcing member is connected to another of the first mounting frames.

9. The manned aircraft frame according to claim 8, characterized in that, The second beam includes a connecting truss, a third reinforcing member, and a fourth reinforcing member, which are connected sequentially. The connecting truss extends along the second direction. The end of the third reinforcing member away from the connecting truss is inclined toward the first reinforcing member and is connected to the same first mounting frame as the first reinforcing member. The end of the fourth reinforcing member away from the connecting truss is inclined toward the second reinforcing member and is connected to another first mounting frame as the second reinforcing member.

10. The manned aircraft frame according to claim 1, characterized in that, The manned spacecraft frame also includes a support component and two fasteners. The two fasteners are respectively connected to the two mounting components. Both fasteners are connected to the support component. The support component is located on the same side of the two mounting components in a third direction. The third direction intersects the plane defined by the first direction and the second direction.

11. The manned aircraft frame according to claim 10, characterized in that, The manned aircraft frame also includes two stabilizing components, each of which is connected at both ends to one of the two fixing components, and the two stabilizing components are respectively fixed to the two ribs.

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

Images