Stiffened frame structure, flying frame assembly, and flying vehicle

Abstract

The application discloses a reinforcing frame structure, a flight frame assembly and a flight vehicle, and relates to the technical field of aircrafts. The reinforcing frame structure is applied to a flight frame, the flight frame is connected above a flight cabin and has an outwardly extending mounting portion, and the mounting portion is connected with a rotorcraft arm. The reinforcing frame structure is arranged in an inner cavity of the mounting portion and comprises a first frame body and a second frame body. The first frame body vertically extends and is connected with a vertical inner side wall of the mounting portion. The second frame body horizontally extends and is connected with a horizontal inner side wall of the mounting portion. A thickened entity portion for penetrating a connecting piece is arranged in the middle of the second frame body, so that the second frame body is locked to the flight cabin through the connecting piece. According to the scheme, the reinforcing frame structure is used to reinforce the mounting portion, and the multi-directional load generated by the rotorcraft arm is transmitted to the flight cabin through the connecting piece, so that the bearing capacity of the flight frame to the load can be improved, and the thickened entity portion forms a local reinforcing effect on a key stress position where the connecting piece is arranged.

Description

Technical Field

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

[0002] With the development of transportation technology, flying cars and other flying vehicles have emerged. The widespread use of flying vehicles helps to solve traffic congestion and alleviate urban traffic pressure.

[0003] Aircraft typically consist of a frame and a passenger cabin. The frame is connected above the cabin, and rotor arms are mounted on the frame to provide lift for flight via rotors on the rotor arms. In existing structures, the outer portion of the frame used to mount the rotor arms is usually made of thin-walled sheet metal or a single aluminum profile, with its internal cavity empty, relying solely on the frame's outer shell for rigidity. Because this outer portion of the frame needs to withstand the multi-directional loads transmitted by the rotor arms, the thin-walled structure is prone to problems such as localized warping and fatigue cracks during long-term use. This will adversely affect the overall structural stability of the frame and the flight safety of the aircraft. Utility Model Content

[0004] The main objective of this application is to propose a reinforced frame structure that addresses the technical problem of insufficient structural strength in the extended portion of the existing aircraft frame used to mount the rotor arm, making it difficult to withstand the multi-directional loads transmitted by the rotor arm over a long period, which can easily lead to a decrease in the overall structural stability of the aircraft frame and the flight safety of the aircraft.

[0005] To achieve the above objectives, the reinforcing frame structure proposed in this application is applied to a flight frame, which is connected above the flight cockpit. The flight frame has an outwardly extending mounting portion for connecting a rotor arm.

[0006] The reinforcing frame structure is disposed in the inner cavity of the mounting portion, and the reinforcing frame structure includes:

[0007] A first frame extends vertically; the first frame is connected to the vertical inner wall of the mounting portion;

[0008] The second frame extends horizontally; one end of the second frame is connected to the lower end of the first frame, and the second frame is connected to the horizontal inner wall of the mounting part; the middle part of the second frame is provided with a thickened solid part, which is used to pass through a connector to lock the second frame to the flight cockpit through the connector.

[0009] In one embodiment, the first frame includes a first upper wall panel, a first lower wall panel, a first left wall panel, and a first right wall panel; the first left wall panel and the first right wall panel are spaced apart in the horizontal direction, the first upper wall panel is connected to the upper side of the first left wall panel and the upper side of the first right wall panel, and the first lower wall panel is connected to the lower side of the first left wall panel and the lower side of the first right wall panel; one end of the second frame is connected to the lower part of the first lower wall panel.

[0010] In one embodiment, the second frame includes a second upper wall panel, a second lower wall panel, a second left wall panel, and a second right wall panel; the second left wall panel and the second right wall panel are spaced apart in the horizontal direction; the second upper wall panel is connected to the upper side of the second left wall panel and the upper side of the second right wall panel; the second lower wall panel is connected to the lower side of the second left wall panel and the lower side of the second right wall panel; the upper side of the thickened solid portion is connected to the second upper wall panel, and the lower side of the thickened solid portion is connected to the second lower wall panel; the lower end of the first frame is connected to the upper part of the second upper wall panel.

[0011] In one embodiment, the second upper wall panel is provided with a correction groove, and the correction groove is provided with a connecting through hole, which extends through the thickened solid portion to the second lower wall panel; the connecting through hole is used to pass through a connecting bolt, which is used to lock onto the flight cockpit, and the head of the connecting bolt is attached to the groove wall of the correction groove.

[0012] In one embodiment, the thickness of the first upper wall plate is 1.1 mm to 1.3 mm.

[0013] In one embodiment, the thickness of the first left wall panel is 1.1 mm to 1.3 mm.

[0014] In one embodiment, the thickness of the first right wall panel is 1.1 mm to 1.3 mm.

[0015] In one embodiment, the first frame further includes a first middle partition, the upper part of the first middle partition is connected to the first upper wall panel, the lower part of the first middle partition is connected to the first lower wall panel, the left side of the first middle partition is connected to the first left wall panel, and the right side of the first middle partition is connected to the first right wall panel.

[0016] In one embodiment, the second frame further includes a second partition plate, the upper part of which is connected to the second upper wall panel, the lower part of which is connected to the second lower wall panel, the left side of which is connected to the second left wall panel, and the right side of which is connected to the thickened solid part.

[0017] In one embodiment, the second frame further includes a third partition plate, the upper part of which is connected to the second upper wall panel, the lower part of which is connected to the second lower wall panel, the left side of which is connected to the thickened solid part, and the right side of which is connected to the second right wall panel.

[0018] In one embodiment, the second frame further includes a first rib, the upper side of which is connected to the second upper wall panel, the lower side of which is connected to the second lower wall panel, and the rear side of which is connected to the thickened solid portion.

[0019] In one embodiment, the second frame further includes a second rib, the upper side of which is connected to the second upper wall panel, the lower side of which is connected to the second lower wall panel, and the front side of which is connected to the thickened solid portion.

[0020] In one embodiment, the second frame further includes a third rib, the upper part of which is connected to the second upper wall panel, the lower part of which is connected to the second lower wall panel, and the rear part of which is connected to the second middle partition. The third rib is located below the first frame.

[0021] In one embodiment, the second frame further includes a fourth rib, the upper part of which is connected to the second upper wall panel, the lower part of which is connected to the second lower wall panel, and the front part of which is connected to the second middle partition. The fourth rib is located below the first frame.

[0022] In one embodiment, the thickness of the second upper wall plate gradually decreases in the direction away from the thickened solid portion.

[0023] In one embodiment, the thickness of the second lower wall plate gradually decreases in the direction away from the thickened solid portion.

[0024] In one embodiment, the thickness of the second partition plate gradually decreases in the direction away from the thickened solid portion.

[0025] In one embodiment, the thickness of the third partition plate gradually decreases in the direction away from the thickened solid portion.

[0026] In one embodiment, the thickness of the first partition plate is 1.1 mm to 1.3 mm.

[0027] In one embodiment, the thickness of the first rib is 1.1 mm to 1.3 mm.

[0028] In one embodiment, the thickness of the second rib is 1.1 mm to 1.3 mm.

[0029] In one embodiment, the thickness of the third rib is 1.1 mm to 1.3 mm.

[0030] In one embodiment, the thickness of the fourth rib is 1.1 mm to 1.3 mm.

[0031] In one embodiment, the second upper wall panel is sequentially divided into a first upper panel segment, a second upper panel segment, and a third upper panel segment along a direction moving to the right away from the thickened solid portion. The thickened solid portion is located within the horizontal projection area of ​​the first upper panel segment. The thickness of the first upper panel segment is 2.9 mm to 3.1 mm, the thickness of the second upper panel segment is 1.9 mm to 2.1 mm, and the thickness of the third upper panel segment is 0.9 mm to 1.1 mm.

[0032] In one embodiment, the second lower wall panel is divided into a first lower plate segment and a second lower plate segment in a direction moving to the left away from the thickened solid portion. The thickness of the first lower plate segment is 1.9 mm to 2.1 mm, and the thickness of the second lower plate segment is 1.1 mm to 1.3 mm.

[0033] In one embodiment, the second lower wall panel is divided into a third lower plate segment and a fourth lower plate segment in a direction moving to the right away from the thickened solid portion. The thickness of the third lower plate segment is 1.9 mm to 2.1 mm, and the thickness of the fourth lower plate segment is 1.1 mm to 1.3 mm.

[0034] In one embodiment, the second partition plate is divided into a first middle plate segment and a second middle plate segment in a direction moving to the left away from the thickened solid portion. The thickness of the first middle plate segment is 2.9 mm to 3.1 mm, and the thickness of the second middle plate segment is 1.5 mm to 1.7 mm.

[0035] In one embodiment, the third partition plate is divided into a third middle plate segment and a fourth middle plate segment in a direction moving to the right away from the thickened solid portion. The thickness of the third middle plate segment is 1.5 mm to 1.7 mm, and the thickness of the fourth middle plate segment is 1.1 mm to 1.3 mm.

[0036] In one embodiment, the first frame and the second frame are configured as an integral part formed by CNC milling.

[0037] In one embodiment, the first frame and the second frame are made of aluminum alloy.

[0038] This application also proposes a flight frame assembly, which includes a flight frame and a reinforcing frame structure as described above.

[0039] This application also proposes an air vehicle comprising a flight cockpit and a flight frame assembly as described above.

[0040] This application's solution uses a first frame and a second frame to form an L-shaped reinforcing frame structure. This reinforcing frame structure is built into the mounting section on the aircraft frame for connecting the rotor arm. This reinforces the mounting section, increasing its structural strength and reducing deformation under the multi-directional loads of the rotor arm. Furthermore, a connector links the reinforcing frame structure to the flight cockpit below the aircraft frame, allowing the multi-directional loads generated by the rotor arm to be transferred sequentially through the mounting section, the reinforcing frame structure, and the connector to the flight cockpit. This effectively distributes the load, thereby... This design improves the overall load-bearing and resistance capabilities of the aircraft frame. Furthermore, it locally thickens the areas on the reinforcing frame structure where connectors are installed, creating a significantly thicker solid section than other parts. This thickened solid section provides targeted reinforcement to critical load-bearing areas of the reinforcing frame structure, reducing stress concentration and improving the overall fatigue strength of the reinforcing frame structure. Other non-critical load-bearing areas of the reinforcing frame structure do not require thickening, thus avoiding the increased weight and disadvantages to lightweight design caused by overall thickening. Attached Figure Description

[0041] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0042] Figure 1 A three-dimensional structural diagram of an embodiment of the reinforcing frame structure provided in this application;

[0043] Figure 2 A front view schematic diagram of an embodiment of the reinforcing frame structure provided in this application;

[0044] Figure 3 for Figure 2 Schematic diagram of the cross-sectional structure along the middle AA;

[0045] Figure 4 An exploded structural diagram of an embodiment of the flight vehicle provided in this application;

[0046] Figure 5 A cross-sectional structural schematic diagram of an embodiment of the flight vehicle provided in this application;

[0047] Figure 6 A schematic diagram of the overall structure of an embodiment of the flight vehicle provided in this application;

[0048] Figure 7 for Figure 6 A magnified schematic diagram of the internal structure at point B.

[0049] Explanation of icon numbers:

[0050] 1000. Reinforced frame structure;

[0051] 2000, Aircraft frame; 2100, Installation section;

[0052] 3000, flight cockpit; 4000, rotor arms;

[0053] 1. First frame; 101. First upper wall panel; 102. First lower wall panel; 103. First left wall panel; 104. First right wall panel; 105. First middle partition;

[0054] 2. Second frame; 201. Thickened solid part; 202. Second upper wall panel; 203. Second lower wall panel; 204. Second left wall panel; 205. Second right wall panel; 206. Connecting through hole; 207. Second middle partition plate; 208. Third middle partition plate; 209. First rib plate; 210. Second rib plate; 211. Third rib plate; 212. Fourth rib plate;

[0055] 2021. The first upper plate section; 2022. The second upper plate section; 2023. The third upper plate section; 2024. Correction slot;

[0056] 2031. First lower plate section; 2032. Second lower plate section; 2033. Third lower plate section; 2034. Fourth lower plate section;

[0057] 2071. The first middle plate section; 2072. The second middle plate section;

[0058] 2081, Third Middle Plate Section; 2082, Fourth Middle Plate Section;

[0059] 3. Connecting parts; 31. Connecting bolts.

[0060] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0061] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of the embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0062] It should be noted that if the embodiments of this application involve directional indicators (such as up, down, left, right, front, back, etc.), the directional indicators are only used to explain the relative positional relationship and movement of the components in a specific posture. If the specific posture changes, the directional indicators will also change accordingly.

[0063] Furthermore, if the embodiments of this application involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the use of "and / or" or "and / or" throughout the text includes three parallel solutions. For example, "A and / or B" includes solution A, solution B, or a solution that simultaneously satisfies A and B. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed in this application.

[0064] With the development of transportation technology, flying cars and other flying vehicles have emerged. The widespread use of flying vehicles helps to solve traffic congestion and alleviate urban traffic pressure.

[0065] Aircraft typically consist of a frame and a passenger cabin. The frame is connected above the cabin, and rotor arms are mounted on the frame to provide lift for flight via rotors on the rotor arms. In existing structures, the outer portion of the frame used to mount the rotor arms is usually made of thin-walled sheet metal or a single aluminum profile, with its internal cavity empty, relying solely on the frame's outer shell for rigidity. Because this outer portion of the frame needs to withstand the multi-directional loads transmitted by the rotor arms, the thin-walled structure is prone to problems such as localized warping and fatigue cracks during long-term use. This will adversely affect the overall structural stability of the frame and the flight safety of the aircraft.

[0066] To address the aforementioned issues, this application proposes a reinforced frame structure, a flight frame assembly, and an air vehicle. The reinforced frame structure is integrated into the mounting portion of the aircraft frame used to connect the rotor arms. This reinforces the mounting portion, and the reinforced frame structure is connected to the flight cockpit below the aircraft frame via connectors. This allows the multi-directional loads generated by the rotor arms to be transferred sequentially to the flight cockpit through the reinforced frame structure and connectors, effectively distributing the loads and improving the overall load-bearing and resistance capabilities of the aircraft frame. Furthermore, the locations on the reinforced frame structure where connectors are inserted are locally thickened to reduce stress concentration at these key load-bearing locations, thereby improving the overall fatigue strength of the reinforced frame structure.

[0067] In the embodiments of this application, the flying vehicle includes, but is not limited to, ordinary ground vehicles, flying cars, passenger planes, helicopters, small aircraft, aircraft, eVTOL (Electric Vertical Take-off and Landing) vehicles, etc.

[0068] It should be noted that if the directional features of up, down, left, right, front, and back are mentioned in the subsequent description of this application, they shall be understood in accordance with the conventional directions of up, down, left, right, front, and back of vehicles such as cars and aircraft, and will not be elaborated further.

[0069] Please refer to Figure 4 and Figure 6 Taking an aircraft as an example, the aircraft includes a main structure, which refers to the main frame, chassis and shell of the aircraft. The main structure includes a flight cabin 3000, which can carry people. It can be understood that the aircraft can be set up as a manned aircraft.

[0070] A flight frame assembly is located above the flight cockpit 3000. The flight frame assembly includes a flight frame 2000 and a connecting beam structure. The connecting beam structure is located on the rear side of the flight frame 2000 and is used to connect the flight frame 2000 and the flight cockpit 3000.

[0071] Please see Figure 1 and supplementary reference Figures 4 to 7 The reinforcing frame structure 1000 provided in one embodiment of this application is applied to the flight frame 2000. The flight frame 2000 is connected above the flight cockpit 3000. The flight frame 2000 has an outwardly extending mounting portion 2100 for connecting the rotor arm 4000.

[0072] The reinforcing frame structure 1000 is disposed in the inner cavity of the mounting portion 2100, and the reinforcing frame structure 1000 includes:

[0073] The first frame 1 extends vertically; the first frame 1 is connected to the vertical inner wall of the mounting part 2100;

[0074] The second frame 2 extends horizontally; one end of the second frame 2 is connected to the lower end of the first frame 1, and the second frame 2 is connected to the horizontal inner wall of the mounting part 2100; a thickened solid part 201 is provided in the middle of the second frame 2, and the thickened solid part 201 is used to pass through the connector 3 so as to lock the second frame 2 to the flight cockpit 3000 through the connector 3.

[0075] In this embodiment, the flight frame 2000 may be provided with multiple outwardly extending mounting portions 2100, each mounting portion 2100 being used to connect to a rotor arm 4000; one end of the rotor arm 4000 may be movable relative to the flight frame 2000, for example, by means of a rotating connection or a telescopic connection, so that the rotor arm 4000 can be extended or retracted relative to the flight frame 2000; the other end of the rotor arm 4000 is connected to the flight rotor to form a multi-rotor structure. Figure 4 and Figure 6 As shown in the example, the flight frame 2000 has four outwardly extending mounting parts 2100. The four mounting parts 2100 extend to the left front, right front, left rear and right rear respectively, so that the flight frame 2000 has an overall X-shaped structure. Four rotor arms 4000 are connected to the four mounting parts 2100 to form a quadcopter.

[0076] The mounting section 2100 can be made of thin-walled sheet metal or integral aluminum profile to form a tubular structure with an internal cavity.

[0077] The first frame 1 and the second frame 2 can be integrally formed by machining or other methods to form a structure such as Figure 1 The L-shaped structure shown. Both the first frame 1 and the second frame 2 can include multiple wall panels to form a frame structure with cavities by enclosing the multiple wall panels. In this way, the basic structural strength of the reinforced frame structure 1000 can be guaranteed while maintaining the lightweight of the reinforced frame structure 1000.

[0078] Multiple riveting holes can be provided on the first frame 1 to connect the first frame 1 to the vertical inner wall of the mounting part 2100 by riveting; similarly, multiple riveting holes can be provided on the second frame 2 to connect the second frame 2 to the horizontal inner wall of the mounting part 2100 by riveting. Based on the above configuration, the reinforcing frame structure 1000 can be connected and fixed in the inner cavity of the mounting part 2100, thereby strengthening the mounting part 2100, improving the structural strength of the mounting part 2100, and reducing the deformation of the mounting part 2100 under the multi-directional load of the rotor arm 4000.

[0079] The thickened solid portion 201 is a localized thickening part in the second frame 2, and its thickness is significantly higher than the wall thickness of other parts of the second frame 2. A through-hole structure extending vertically through the thickened solid portion 201 can be provided. This through-hole structure is positioned opposite to the front side of the flight cockpit 3000 below. This through-hole structure can be used to pass through bolts or other connecting parts 3, allowing the connecting parts 3 to pass sequentially through the through-hole structure, the clearance holes on the mounting portion 2100, and lock onto the corresponding parts of the flight cockpit 3000. Thus, the connection and fixation between the reinforcing frame structure 1000, the mounting portion 2100, and the flight cockpit 3000 can be achieved through the connecting parts 3. For example, if the reinforcing frame structure 1000 is installed in the mounting portion 2100 extending along the left front, the connector 3 passing through the reinforcing frame structure 1000 can be locked to the A-pillar on the left front side of the flight cockpit 3000; similarly, if the reinforcing frame structure 1000 is installed in the mounting portion 2100 extending along the right front, the connector 3 passing through the reinforcing frame structure 1000 can be locked to the A-pillar on the right front side of the flight cockpit 3000.

[0080] Based on the above configuration, when the flight frame 2000 is connected to the flight cockpit 3000 via the rear connecting beam structure, the connection support between the flight frame 2000 and the flight cockpit 3000 can be increased by the connector 3 passing through the reinforcing frame structure 1000. This increases the load transmission path, allowing the multi-directional loads generated by the rotor arm 4000 to be transmitted sequentially through the mounting part 2100, the reinforcing frame structure 1000, and the connector 3 to the flight cockpit 3000 below. This effectively disperses the loads and improves the overall load-bearing and resistance capacity of the flight frame 2000 to multi-directional loads. Meanwhile, since the location of the connector 3 is the main stress-bearing area, the part of the reinforcing frame structure 1000 used for the connector 3 is also thickened to form a thickened solid part 201 with a significantly higher thickness than other parts. This can provide targeted structural reinforcement to the key stress-bearing parts of the reinforcing frame structure 1000, reduce stress concentration in these key stress-bearing parts, and improve the overall fatigue strength of the reinforcing frame structure 1000. However, other non-critical stress-bearing parts of the reinforcing frame structure 1000 do not need to be thickened, thus avoiding the problem of increased weight and disadvantages to lightweight design caused by overall thickening.

[0081] Therefore, in this embodiment, an L-shaped reinforcing frame structure 1000 is formed by the first frame 1 and the second frame 2. This reinforcing frame structure 1000 is built into the mounting portion 2100 on the flight frame 2000 for connecting the rotor arm 4000. In this way, the reinforcing frame structure 1000 can strengthen the mounting portion 2100, improve the structural strength of the mounting portion 2100, and reduce the deformation of the mounting portion 2100 under the multi-directional load of the rotor arm 4000. On this basis, the reinforcing frame structure 1000 is connected to the flight cockpit 3000 below the flight frame 2000 by the connector 3, so that the multi-directional load generated by the rotor arm 4000 is transferred sequentially through the mounting portion 2100, the reinforcing frame structure 1000, and the connector 3 to the cockpit. The flight cockpit 3000 effectively distributes the load, thereby improving the overall load-bearing and resistance capabilities of the flight frame 2000. In addition, this embodiment also locally thickens the positions on the reinforcing frame structure 1000 where the connecting parts 3 are inserted, forming a thickened solid part 201 with a significantly higher thickness than other parts. This thickened solid part 201 can provide targeted reinforcement to the key stress-bearing parts of the reinforcing frame structure 1000, reducing stress concentration in these key stress-bearing parts and improving the overall fatigue strength of the reinforcing frame structure 1000. Other non-critical stress-bearing parts on the reinforcing frame structure 1000 do not need to be thickened, thus avoiding the problem of increased weight and disadvantages to lightweight design caused by overall thickening.

[0082] In one embodiment, refer to Figure 1 and Figure 2 The first frame 1 includes a first upper wall panel 101, a first lower wall panel 102, a first left wall panel 103, and a first right wall panel 104; the first left wall panel 103 and the first right wall panel 104 are spaced apart in the horizontal direction, the first upper wall panel 101 is connected to the upper side of the first left wall panel 103 and the upper side of the first right wall panel 104, and the first lower wall panel 102 is connected to the lower side of the first left wall panel 103 and the lower side of the first right wall panel 104; one end of the second frame 2 is connected to the lower part of the first lower wall panel 102.

[0083] In this embodiment, the first upper wall panel 101, the first lower wall panel 102, the first left wall panel 103 and the first right wall panel 104 are enclosed to form a frame-like structure with a cavity. In this way, the basic structural strength of the first frame 1 can be guaranteed by utilizing the properties of the frame-like structure, while avoiding excessive material usage in the first frame 1, thus maintaining the overall lightweight of the reinforced frame structure 1000.

[0084] In one embodiment, refer to Figure 1 and Figure 2The second frame 2 includes a second upper wall panel 202, a second lower wall panel 203, a second left wall panel 204, and a second right wall panel 205; the second left wall panel 204 and the second right wall panel 205 are spaced apart in the horizontal direction; the second upper wall panel 202 is connected to the upper side of the second left wall panel 204 and the upper side of the second right wall panel 205; the second lower wall panel 203 is connected to the lower side of the second left wall panel 204 and the lower side of the second right wall panel 205; the upper side of the thickened solid part 201 is connected to the second upper wall panel 202, and the lower side of the thickened solid part 201 is connected to the second lower wall panel 203; the lower end of the first frame 1 is connected to the upper part of the second upper wall panel 202.

[0085] In this embodiment, the second upper wall panel 202, the second lower wall panel 203, the second left wall panel 204 and the second right wall panel 205 are enclosed to form a frame-like structure with a cavity. This can utilize the properties of the frame-like structure to ensure the basic structural strength of the second frame 2, while avoiding excessive material usage in the second frame 2, thus maintaining the overall lightweight of the reinforcing frame structure 1000.

[0086] It is understandable that, such as Figure 1 and Figure 2 As shown, when the first frame 1 includes a first upper wall panel 101, a first lower wall panel 102, a first left wall panel 103, and a first right wall panel 104, and the second frame 2 includes a second upper wall panel 202, a second lower wall panel 203, a second left wall panel 204, and a second right wall panel 205, the first lower wall panel 102 and the second upper wall panel 202 partially overlap. In this case, the first lower wall panel 102 and the second upper wall panel 202 can share the same wall panel structure.

[0087] In one embodiment, refer to Figure 1 , Figure 3 and Figure 5 The second upper wall panel 202 is provided with a correction groove 2024, and a connecting through hole 206 is provided in the correction groove 2024. The connecting through hole 206 extends through the thickened solid part 201 to the second lower wall panel 203. The connecting through hole 206 is used to pass through the connecting bolt 31, which is used to lock onto the flight cockpit 3000. The head of the connecting bolt 31 is attached to the groove wall of the correction groove 2024.

[0088] In this embodiment, the connecting member 3 is a connecting bolt 31. In practical applications, since the mounting points for the connecting bolts 31 on the reinforcing frame structure 1000 are located at a relatively deep position, to reduce assembly errors, before installing the reinforcing frame structure 1000 into the mounting part 2100, a small initial through hole (the diameter of the initial through hole can be set to φ3.2mm) can be first opened in the second upper wall plate 202. The initial through hole penetrates downwards through the thickened solid part 201 to the second lower wall plate 203. Simultaneously, the side walls of the mounting part 2100 and the flight cockpit 3000 should also be... A mating hole is made at the corresponding position; after the reinforcing frame structure 1000 is installed into the inner cavity of the mounting part 2100, the initial through hole of the reinforcing frame structure 1000 is aligned with the mating holes of the mounting part 2100 and the flight cockpit 3000, and then the initial through hole and the mating hole are enlarged together under the same reference; the initial through hole after the enlargement process constitutes the final connecting through hole 206, the diameter of the connecting through hole 206 can be set to φ8mm, and the connecting through hole 206 can maintain a high coaxiality with the mating hole after the enlargement process.

[0089] After completing the above-mentioned hole enlargement process, the upper side of the second upper wall plate 202 should be milled and ground, using the enlarged connecting through hole 206 as a reference, to process the correction groove 2024 on the second upper wall plate 202. The bottom wall of the correction groove 2024 is perpendicular to the axis of the connecting through hole 206. In this way, after the connecting bolt 31 is passed through the connecting through hole 206 and the mating hole in sequence and locked into the corresponding area of ​​the flight cockpit 3000, it can be ensured that the end face of the head of the connecting bolt 31 has a high degree of parallelism with the bottom wall of the correction groove 2024, so that the end face of the head of the connecting bolt 31 can fully fit with the bottom wall of the correction groove 2024.

[0090] Based on the aforementioned enlargement operation of the connecting through hole 206 and the setting of the correction groove 2024, dimensional deviations existing in the production and assembly processes can be eliminated to the greatest extent, ensuring a high degree of coaxiality between the connecting through hole 206 and the mating holes on the mounting part 2100 and the flight cockpit 3000, and ensuring that the head of the connecting bolt 31 can fully fit with the groove wall of the correction groove 2024. This improves the installation and fitting accuracy between the reinforcing frame structure 1000 and the mounting part 2100 and the flight cockpit 3000, which is conducive to further improving the structural stability of the flight frame 2000 and the flight safety of the aircraft.

[0091] In one embodiment, refer to Figures 1 to 3 The first frame 1 also includes a first middle partition 105. The upper part of the first middle partition 105 is connected to the first upper wall panel 101, the lower part of the first middle partition 105 is connected to the first lower wall panel 102, the left side of the first middle partition 105 is connected to the first left wall panel 103, and the right side of the first middle partition 105 is connected to the first right wall panel 104.

[0092] By setting the first partition plate 105, a supporting effect can be formed in the cavity enclosed by the first upper wall plate 101, the first lower wall plate 102, the first left wall plate 103 and the first right wall plate 104, thereby improving the structural strength of the first frame 1.

[0093] In one embodiment, refer to Figures 1 to 3 The second frame 2 also includes a second partition plate 207. The upper part of the second partition plate 207 is connected to the second upper wall panel 202, the lower part of the second partition plate 207 is connected to the second lower wall panel 203, the left side of the second partition plate 207 is connected to the second left wall panel 204, and the right side of the second partition plate 207 is connected to the thickened solid part 201.

[0094] In one embodiment, refer to Figures 1 to 3 The second frame 2 also includes a third partition 208. The upper part of the third partition 208 is connected to the second upper wall panel 202, the lower part of the third partition 208 is connected to the second lower wall panel 203, the left side of the third partition 208 is connected to the thickened solid part 201, and the right side of the third partition 208 is connected to the second right wall panel 205.

[0095] By setting the second partition 207 and the third partition 208, a supporting effect can be formed in the cavity enclosed by the second upper wall panel 202, the second lower wall panel 203, the second left wall panel 204 and the second right wall panel 205, and an additional reinforcement effect can be provided for the thickened solid part 201, thereby improving the overall structural strength of the second frame 2 and further reducing the stress concentration of the thickened solid part 201.

[0096] In one embodiment, refer to Figures 1 to 3 The second frame 2 also includes a first rib 209, the upper part of the first rib 209 is connected to the second upper wall panel 202, the lower part of the first rib 209 is connected to the second lower wall panel 203, and the rear part of the first rib 209 is connected to the thickened solid part 201.

[0097] By setting the first rib 209, on the one hand, it can form a supporting effect between the second upper wall plate 202 and the second lower wall plate 203, and on the other hand, it can act as a reinforcing rib to provide additional reinforcement to the front side of the thickened solid part 201, thereby further improving the overall structural strength of the second frame 2 and reducing the stress concentration of the thickened solid part 201.

[0098] In one embodiment, refer to Figures 1 to 3 The second frame 2 also includes a second rib 210, the upper part of the second rib 210 is connected to the second upper wall panel 202, the lower part of the second rib 210 is connected to the second lower wall panel 203, and the front part of the second rib 210 is connected to the thickened solid part 201.

[0099] By setting the second rib 210, on the one hand, it can form a supporting effect between the second upper wall plate 202 and the second lower wall plate 203, and on the other hand, it can act as a reinforcing rib to provide additional reinforcement to the rear side of the thickened solid part 201, thereby further improving the overall structural strength of the second frame 2 and reducing the stress concentration of the thickened solid part 201.

[0100] In one embodiment, refer to Figures 1 to 3 The second frame 2 also includes a third rib 211. The upper part of the third rib 211 is connected to the second upper wall panel 202, the lower part of the third rib 211 is connected to the second lower wall panel 203, and the rear part of the third rib 211 is connected to the second middle partition 207. The third rib 211 is located below the first frame 1.

[0101] By setting the third rib 211, a supporting effect can be formed between the front side of the second upper wall panel 202, the second lower wall panel 203 and the second middle partition 207, thereby further improving the overall structural strength of the second frame 2.

[0102] In one embodiment, refer to Figures 1 to 3 The second frame 2 also includes a fourth rib 212. The upper part of the fourth rib 212 is connected to the second upper wall panel 202, the lower part of the fourth rib 212 is connected to the second lower wall panel 203, and the front part of the fourth rib 212 is connected to the second middle partition 207. The fourth rib 212 is located below the first frame 1.

[0103] By setting the fourth rib 212, a supporting effect can be formed between the rear side of the second upper wall panel 202, the second lower wall panel 203 and the second middle partition 207, thereby further improving the overall structural strength of the second frame 2.

[0104] In one embodiment, refer to Figures 1 to 3 The thickness of the second upper wall panel 202 gradually decreases in the direction away from the thickened solid part 201.

[0105] In one embodiment, refer to Figures 1 to 3 The thickness of the second lower wall panel 203 gradually decreases in the direction away from the thickened solid part 201.

[0106] In one embodiment, refer to Figures 1 to 3 The thickness of the second partition 207 gradually decreases in the direction away from the thickened solid part 201.

[0107] In one embodiment, refer to Figures 1 to 3 The thickness of the third partition 208 gradually decreases in the direction away from the thickened solid part 201.

[0108] In practical applications, since the area where the thickened solid part 201 is located needs to withstand a large load, structural reinforcement of the area near the thickened solid part 201 is the most efficient way to improve the overall structural performance of the reinforced frame structure 1000. Based on this consideration, the above embodiment sets the second upper wall panel 202, the second lower wall panel 203, the second middle partition 207, and the third middle partition 208 to have varying wall thicknesses at different locations; specifically as follows... Figure 1 As shown, the thickness of the second upper wall panel 202 gradually decreases along the direction away from the thickened solid portion 201 to the right; the thickness of the second lower wall panel 203 gradually decreases along the direction away from the thickened solid portion 201 to the left; the thickness of the second middle partition 207 gradually decreases along the direction away from the thickened solid portion 201 to the left; and the thickness of the third middle partition 208 gradually decreases along the direction away from the thickened solid portion 201 to the right. This optimizes the overall structure of the reinforced frame structure 1000, utilizing the thicker portions of each wall panel to provide efficient local reinforcement to the thickened solid portion 201. For the portions of each wall panel that are far from the thickened solid portion 201 and have a limited effect on improving the overall structural performance, corresponding thinning treatment is performed to reduce weight. Thus, lightweight design can be achieved while meeting the load-bearing requirements of the reinforced frame structure 1000.

[0109] The thickness of the second upper wall panel 202, the second lower wall panel 203, the second middle partition 207, and the third middle partition 208 may decrease in a stepwise or linear manner along the direction away from the thickened solid part 201, and this is not limited here.

[0110] Furthermore, referring to Figure 1 The second upper wall panel 202 is divided into a first upper panel segment 2021, a second upper panel segment 2022 and a third upper panel segment 2023 in a direction moving to the right away from the thickened solid part 201. The thickened solid part 201 is located in the horizontal projection area of ​​the first upper panel segment 2021, that is, the connector 3 is installed within the coverage area of ​​the first upper panel segment 2021. Based on this configuration, the first upper plate segment 2021 is closest to the thickened solid portion 201, and its thickness can be set to 2.9mm to 3.1mm, preferably 3mm; the second upper plate segment 2022 is farther from the thickened solid portion 201 than the first upper plate segment 2021, and its thickness can be set to 1.9mm to 2.1mm, preferably 2mm; the third upper plate segment 2023 is farther from the thickened solid portion 201 than the second upper plate segment 2022, and its thickness can be set to 0.9mm to 1.1mm, preferably 1mm.

[0111] Based on the above settings, the different parts of the second upper wall panel 202 can be set with different wall thicknesses according to the difference in the degree of improvement of the overall structural performance of the different parts of the second upper wall panel 202, so that the second upper wall panel 202 forms a stepped structure with gradually changing thickness. The part closer to the critical stress area has a thicker wall thickness, while the part farther away from the critical stress area has a thinner wall thickness. In this way, lightweight design can be achieved while meeting the load-bearing requirements of the reinforced frame structure 1000.

[0112] Furthermore, referring to Figure 1 The second lower wall panel 203 is divided into a first lower plate segment 2031 and a second lower plate segment 2032 in a direction moving to the left away from the thickened solid portion 201. The first lower plate segment 2031 is closest to the thickened solid portion 201, and its thickness can be set to 1.9mm to 2.1mm, preferably 2mm. The second lower plate segment 2032 is farther from the thickened solid portion 201 than the first lower plate segment 2031, and its thickness can be set to 1.1mm to 1.3mm, preferably 1.2mm.

[0113] The second lower wall panel 203 is divided into a third lower plate segment 2033 and a fourth lower plate segment 2034 in a direction moving to the right away from the thickened solid portion 201. The third lower plate segment 2033 is closest to the thickened solid portion 201, and its thickness can be set to 1.9mm to 2.1mm, preferably 2mm. The fourth lower plate segment 2034 is farther from the thickened solid portion 201 than the third lower plate segment 2033, and its thickness can be set to 1.1mm to 1.3mm, preferably 1.2mm.

[0114] Based on the above settings, the different parts of the second lower wall panel 203 can be set with different wall thicknesses according to the difference in the degree of improvement of the overall structural performance of the different parts of the second lower wall panel 203, so that the second lower wall panel 203 forms a stepped structure with gradually changing thickness. The part closer to the critical stress area has a thicker wall thickness, while the part farther away from the critical stress area has a thinner wall thickness. In this way, lightweight design can be achieved while meeting the load-bearing requirements of the reinforced frame structure 1000.

[0115] Furthermore, referring to Figure 1 The second partition 207 is divided into a first middle plate segment 2071 and a second middle plate segment 2072 in a direction moving to the left away from the thickened solid portion 201. The first middle plate segment 2071 is closest to the thickened solid portion 201, and its thickness can be set to 2.9mm to 3.1mm, preferably 3mm. The second middle plate segment 2072 is farther away from the thickened solid portion 201 than the first middle plate segment 2071, and its thickness can be set to 1.5mm to 1.7mm, preferably 1.6mm.

[0116] In the case where the reinforcing frame structure 1000 includes a third rib 211 and a fourth rib 212, such as Figure 1 and Figure 2 As shown, if the third rib 211 and the fourth rib 212 are flush with each other, the first middle plate segment 2071 and the second middle plate segment 2072 can use the third rib 211 or the fourth rib 212 as the interface.

[0117] Based on the above settings, the different parts of the second partition 207 can be set with different wall thicknesses according to the difference in the degree of improvement of the overall structural performance of the different parts of the second partition 207, so that the second partition 207 forms a stepped structure with gradually changing thickness. The part closer to the critical stress area has a thicker wall thickness, while the part farther away from the critical stress area has a thinner wall thickness. In this way, lightweight design can be achieved while meeting the load-bearing requirements of the reinforced frame structure 1000.

[0118] Furthermore, referring to Figure 1 The third partition 208 is divided into a third middle plate segment 2081 and a fourth middle plate segment 2082 in a direction moving to the right away from the thickened solid portion 201. The third middle plate segment 2081 is closest to the thickened solid portion 201, and its thickness can be set to 1.5mm to 1.7mm, preferably 1.6mm. The fourth middle plate segment 2082 is farther from the thickened solid portion 201 than the third middle plate segment 2081, and its thickness can be set to 1.1mm to 1.3mm, preferably 1.2mm.

[0119] Based on the above settings, the different parts of the third partition 208 can be set with different wall thicknesses according to the difference in the degree of improvement of the overall structural performance of the different parts of the third partition 208, so that the third partition 208 forms a stepped structure with gradually changing thickness. The part closer to the critical stress area has a thicker wall thickness, while the part farther away from the critical stress area has a thinner wall thickness. In this way, lightweight design can be achieved while meeting the load-bearing requirements of the reinforced frame structure 1000.

[0120] In one embodiment, the thickness of the first partition 105 is 1.1 mm to 1.3 mm.

[0121] In one embodiment, the thickness of the first rib 209 is 1.1 mm to 1.3 mm.

[0122] In one embodiment, the thickness of the second rib 210 is 1.1 mm to 1.3 mm.

[0123] In one embodiment, the thickness of the third rib 211 is 1.1 mm to 1.3 mm.

[0124] In one embodiment, the thickness of the fourth rib 212 is 1.1 mm to 1.3 mm.

[0125] In one embodiment, the thickness of the first upper wall panel 101 is 1.1 mm to 1.3 mm.

[0126] In one embodiment, the thickness of the first left wall plate 103 is 1.1 mm to 1.3 mm.

[0127] In one embodiment, the thickness of the first right wall panel 104 is 1.1 mm to 1.3 mm.

[0128] Specifically, refer to Figures 1 to 3 For the first partition plate 105, the first rib plate 209, the second rib plate 210, the third rib plate 211, the fourth rib plate 212, the first upper wall plate 101, the first left wall plate 103, and the first right wall plate 104, they are all far from the key stress-bearing areas such as the thickened solid part 201 or have a small effect on improving the overall structural performance. Therefore, their wall thickness can be uniformly limited to a low level of 1.1mm to 1.3mm, preferably 1.2mm. This can further reduce the weight of the reinforcing frame structure 1000 and achieve lightweight design.

[0129] In one embodiment, refer to Figures 1 to 3 The first frame 1 and the second frame 2 are configured as an integral part formed by CNC milling. CNC milling offers high operational flexibility and does not damage the metallographic structure. Thus, while maintaining the basic structural strength of the reinforcing frame structure 1000, it is convenient to process the reinforcing frame structure 1000 into a structural form with wall thickness differences as described in the above embodiment.

[0130] In one embodiment, refer to Figures 1 to 3 The first frame 1 and the second frame 2 are made of aluminum alloy. Specifically, the first frame 1 and the second frame 2 can be made of a high-strength aluminum alloy and are formed by CNC milling. In this way, the basic structural strength of the reinforcing frame structure 1000 can be guaranteed while the lightweight properties of aluminum alloy can be utilized to maintain the lightweight of the reinforcing frame structure 1000.

[0131] This application also provides a flight frame assembly; please refer to [link / reference]. Figures 4 to 7 The flight frame assembly includes a flight frame 2000 and a reinforcing frame structure 1000 in any of the above embodiments.

[0132] For the specific structure of the reinforcing frame structure 1000, please refer to the description of the above embodiments. Since the flight frame assembly in this embodiment adopts all the technical solutions of all the above embodiments, it at least possesses all the beneficial effects brought about by the technical solutions of the above embodiments. That is, an L-shaped reinforcing frame structure 1000 is formed by the first frame 1 and the second frame 2. This reinforcing frame structure 1000 is built into the mounting portion 2100 on the flight frame 2000 for connecting the rotor arm 4000. Thus, the reinforcing frame structure 1000 can be used to reinforce the mounting portion 2100, improving the structural strength of the mounting portion 2100 and reducing the deformation of the mounting portion 2100 under the multi-directional load of the rotor arm 4000. Furthermore, the reinforcing frame structure 1000 is connected to the flight cockpit 3000 below the flight frame 2000 via the connector 3, so that the multi-directional load generated by the rotor arm 4000 can be sequentially transferred through... The load is transferred to the flight cockpit 3000 via the mounting section 2100, the reinforcing frame structure 1000, and the connector 3, thus effectively distributing the load and improving the overall load-bearing and resistance capabilities of the flight frame 2000. In addition, this solution also locally thickens the area on the reinforcing frame structure 1000 where the connector 3 is inserted, forming a thickened solid part 201 with a significantly higher thickness than other parts. This thickened solid part 201 can provide targeted reinforcement to the key stress-bearing parts of the reinforcing frame structure 1000, reducing stress concentration in these key stress-bearing parts and improving the overall fatigue strength of the reinforcing frame structure 1000. Other non-critical stress-bearing parts on the reinforcing frame structure 1000 do not need to be thickened, thus avoiding the problem of increased weight and disadvantages to lightweight design caused by overall thickening.

[0133] This application also provides an air vehicle; please refer to [link / reference]. Figures 4 to 7 The flying vehicle includes a flight cockpit 3000 and a flight frame assembly as described in any of the above embodiments.

[0134] In this embodiment, flying vehicles include, but are not limited to, ordinary ground vehicles, flying cars, passenger planes, helicopters, small aircraft, aircraft, eVTOL (Electric Vertical Take-off and Landing) vehicles, etc.

[0135] For the specific structure of the flight frame assembly, please refer to the description of the above embodiments. Since the flight vehicle in this embodiment adopts all the technical solutions of all the above embodiments, it has at least all the beneficial effects brought about by the technical solutions of the above embodiments, and will not be elaborated here.

[0136] The above description is merely an exemplary embodiment of this application and does not limit the patent scope of this application. Any equivalent structural transformations made based on the technical concept of this application and the contents of the specification and drawings of this application, or direct / indirect applications in other related technical fields, are included within the patent protection scope of this application.

Claims

1. A reinforcing frame structure, characterized in that, The reinforcing frame structure is applied to the flight frame, which is connected above the flight cockpit. The flight frame has an outwardly extending mounting portion for connecting the rotor arm. The reinforcing frame structure is disposed in the inner cavity of the mounting portion, and the reinforcing frame structure includes: A first frame extends vertically; the first frame is connected to the vertical inner wall of the mounting portion; The second frame extends horizontally; one end of the second frame is connected to the lower end of the first frame, and the second frame is connected to the horizontal inner wall of the mounting part; the middle part of the second frame is provided with a thickened solid part, which is used to pass through a connector to lock the second frame to the flight cockpit through the connector.

2. The reinforcing frame structure according to claim 1, characterized in that, The first frame includes a first upper wall panel, a first lower wall panel, a first left wall panel, and a first right wall panel; the first left wall panel and the first right wall panel are spaced apart in the horizontal direction, the first upper wall panel is connected to the upper side of the first left wall panel and the upper side of the first right wall panel, and the first lower wall panel is connected to the lower side of the first left wall panel and the lower side of the first right wall panel; one end of the second frame is connected to the lower part of the first lower wall panel. And / or, the second frame includes a second upper wall panel, a second lower wall panel, a second left wall panel, and a second right wall panel; the second left wall panel and the second right wall panel are spaced apart in the horizontal direction, the second upper wall panel is connected to the upper side of the second left wall panel and the upper side of the second right wall panel, and the second lower wall panel is connected to the lower side of the second left wall panel and the lower side of the second right wall panel; the upper side of the thickened solid part is connected to the second upper wall panel, and the lower side of the thickened solid part is connected to the second lower wall panel; the lower end of the first frame is connected to the upper part of the second upper wall panel.

3. The reinforcing frame structure according to claim 2, characterized in that, The second upper wall panel is provided with a correction groove, and the correction groove is provided with a connecting through hole. The connecting through hole extends through the thickened solid part to the second lower wall panel. The connecting through hole is used to pass through a connecting bolt, and the connecting bolt is used to lock onto the flight cockpit. The head of the connecting bolt is attached to the groove wall of the correction groove. And / or, the thickness of the first upper wall panel is 1.1mm to 1.3mm; And / or, the thickness of the first left wall plate is 1.1mm to 1.3mm; And / or, the thickness of the first right wall panel is 1.1mm to 1.3mm.

4. The reinforcing frame structure according to claim 2, characterized in that, The first frame also includes a first middle partition, the upper part of the first middle partition is connected to the first upper wall panel, the lower part of the first middle partition is connected to the first lower wall panel, the left side of the first middle partition is connected to the first left wall panel, and the right side of the first middle partition is connected to the first right wall panel. And / or, the second frame further includes a second partition plate, the upper part of the second partition plate is connected to the second upper wall panel, the lower part of the second partition plate is connected to the second lower wall panel, the left side of the second partition plate is connected to the second left wall panel, and the right side of the second partition plate is connected to the thickened solid part. And / or, the second frame further includes a third partition plate, the upper part of which is connected to the second upper wall panel, the lower part of which is connected to the second lower wall panel, the left side of which is connected to the thickened solid part, and the right side of which is connected to the second right wall panel. And / or, the second frame further includes a first rib, the upper part of the first rib is connected to the second upper wall panel, the lower part of the first rib is connected to the second lower wall panel, and the rear part of the first rib is connected to the thickened solid part. And / or, the second frame further includes a second rib, the upper part of which is connected to the second upper wall panel, the lower part of which is connected to the second lower wall panel, and the front part of which is connected to the thickened solid part.

5. The reinforcing frame structure according to claim 4, characterized in that, The second frame also includes a third rib, the upper part of which is connected to the second upper wall panel, the lower part of which is connected to the second lower wall panel, and the rear part of which is connected to the second middle partition. The third rib is located below the first frame. And / or, the second frame further includes a fourth rib, the upper part of which is connected to the second upper wall panel, the lower part of which is connected to the second lower wall panel, the front part of which is connected to the second middle partition, and the fourth rib is located below the first frame.

6. The reinforcing frame structure according to claim 5, characterized in that, The thickness of the second upper wall plate gradually decreases in the direction away from the thickened solid portion; And / or, the thickness of the second lower wall plate gradually decreases in the direction away from the thickened solid portion; And / or, the thickness of the second partition plate gradually decreases in the direction away from the thickened solid portion; And / or, the thickness of the third partition plate gradually decreases in the direction away from the thickened solid portion; And / or, the thickness of the first partition plate is 1.1mm to 1.3mm; And / or, the thickness of the first rib is 1.1mm to 1.3mm; And / or, the thickness of the second rib is 1.1mm to 1.3mm; And / or, the thickness of the third rib is 1.1mm to 1.3mm; And / or, the thickness of the fourth rib is 1.1mm to 1.3mm.

7. The reinforcing frame structure according to claim 6, characterized in that, The second upper wall panel is divided into a first upper panel segment, a second upper panel segment, and a third upper panel segment in a direction moving to the right away from the thickened solid portion. The thickened solid portion is located within the horizontal projection area of ​​the first upper panel segment. The thickness of the first upper panel segment is 2.9 mm to 3.1 mm, the thickness of the second upper panel segment is 1.9 mm to 2.1 mm, and the thickness of the third upper panel segment is 0.9 mm to 1.1 mm. And / or, the second lower wall panel is divided into a first lower plate segment and a second lower plate segment in a direction moving to the left away from the thickened solid portion, the thickness of the first lower plate segment is 1.9mm to 2.1mm, and the thickness of the second lower plate segment is 1.1mm to 1.3mm; And / or, the second lower wall panel is divided into a third lower plate segment and a fourth lower plate segment in a direction moving to the right away from the thickened solid portion, the thickness of the third lower plate segment is 1.9mm to 2.1mm, and the thickness of the fourth lower plate segment is 1.1mm to 1.3mm; And / or, the second partition plate is divided into a first middle plate segment and a second middle plate segment in a direction moving to the left away from the thickened solid portion, wherein the thickness of the first middle plate segment is 2.9mm to 3.1mm and the thickness of the second middle plate segment is 1.5mm to 1.7mm; And / or, the third partition plate is divided into a third middle plate segment and a fourth middle plate segment in a direction moving to the right away from the thickened solid portion, the thickness of the third middle plate segment is 1.5mm to 1.7mm, and the thickness of the fourth middle plate segment is 1.1mm to 1.3mm.

8. The reinforcing frame structure according to any one of claims 1 to 7, characterized in that, The first frame and the second frame are configured as an integral part formed by CNC milling; And / or, the first frame and the second frame are made of aluminum alloy.

9. A flight frame assembly, characterized in that, The flight frame assembly includes a flight frame and a reinforcing frame structure as described in any one of claims 1 to 8.

10. An airborne vehicle, characterized in that, The flight vehicle includes a flight cockpit and a flight frame assembly as described in claim 9.

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