Tow sled system mounting device

Abstract

The application discloses a tail skid system mounting device, which belongs to the technical field of civil aviation engineering and comprises a front reinforcing plate, a rear reinforcing plate, an upper reinforcing plate, a lower reinforcing plate, a first mounting piece, a second mounting piece and a supporting piece. The rear reinforcing plate and the front reinforcing plate are arranged in the mounting groove in a spaced mode and are connected with the fuselage skin. The upper reinforcing plate is located between the front reinforcing plate and the rear reinforcing plate and is connected with the top of the front reinforcing plate and the rear reinforcing plate and the fuselage skin. The lower reinforcing plate is attached to and connected with the fuselage skin. The bottom of the front reinforcing plate and the rear reinforcing plate is connected with the lower reinforcing plate, and the front reinforcing plate, the rear reinforcing plate and the upper reinforcing plate and the lower reinforcing plate form a box type frame. The first mounting piece is arranged on the lower reinforcing plate and is used for rotatingly mounting a friction block assembly. The second mounting piece is fixed on the rear reinforcing plate and is used for rotatingly mounting an actuating cylinder assembly. The supporting piece is located in the box type frame and is fixedly connected with the front reinforcing plate, the rear reinforcing plate, the upper reinforcing plate and the lower reinforcing plate. The application can solve the problem of fuselage structure damage caused by load concentration, thereby ensuring flight safety.

Description

Technical Field

[0001] This invention relates to the field of civil aviation engineering technology, and in particular to a tail skid system mounting device. Background Technology

[0002] Civil transport aircraft must complete minimum takeoff speed test flights before entering operation. These tests verify the minimum takeoff speed parameters of the aircraft under critical conditions, ensuring flight safety and handling stability during takeoff. During minimum takeoff speed test flights, the tail of the aircraft is highly susceptible to contact and friction with the ground, which can damage the fuselage structure.

[0003] To address this issue, the existing technology generally adopts a protective solution of adding a tail skid system to the lower surface of the aircraft. The tail skid system mainly consists of two parts: a friction block assembly and an actuator cylinder assembly. Its installation position is usually selected in the tail skid contact point area of ​​the rear fuselage belly. By utilizing the wear and tear of the friction blocks and the buffering effect of the actuator cylinder, the impact of the ground impact on the fuselage is reduced.

[0004] However, although existing tail skid systems can absorb ground impact and friction energy to a certain extent, they still have significant shortcomings in practical applications. Because the impact and friction loads generated when an aircraft touches the ground are instantaneous and high-intensity, existing tail skid systems can only absorb energy through their own components, lacking an effective load transfer and diffusion mechanism. The inability to evenly and efficiently diffuse the load concentrated on the tail skid system to the overall fuselage structure leads to excessive local loads. This can not only affect the service life of the tail skid system itself, but in severe cases, it can also be transferred to the fuselage structure through the installation area, causing structural stress concentration and potentially damaging the original fuselage structure.

[0005] Therefore, there is an urgent need to provide a tail skid system mounting device to solve the above problems. Summary of the Invention

[0006] The purpose of this invention is to provide a tail skid system mounting device that can solve the problem of fuselage structural damage caused by concentrated loads in the prior art, thereby ensuring the safety of aircraft test flights.

[0007] Based on the above concept, the technical solution adopted by this invention is as follows:

[0008] A tail skid system mounting device is used to mount a tail skid system to the bottom of the fuselage. The bottom of the fuselage has a mounting groove. The tail skid system includes a friction block assembly and an actuator cylinder assembly. The actuator cylinder assembly can drive the friction block assembly to rotate between a retracted position and a working position. The tail skid system mounting device includes:

[0009] Front reinforcement plate;

[0010] The rear reinforcing plate and the front reinforcing plate are arranged parallel to each other and spaced apart in the mounting groove along the length of the fuselage, and are both connected to the fuselage skin;

[0011] An upper reinforcing plate is located between the front reinforcing plate and the rear reinforcing plate and is connected to the top of the front reinforcing plate and the rear reinforcing plate, and the upper reinforcing plate is connected to the fuselage skin;

[0012] The lower reinforcing plate is attached to and connected to the fuselage skin. The bottom of the front reinforcing plate and the rear reinforcing plate are both connected to the lower reinforcing plate, so that the front reinforcing plate, the rear reinforcing plate, the upper reinforcing plate and the lower reinforcing plate together form a box frame, and the box frame is located in the mounting groove.

[0013] The first mounting component is disposed on the side of the lower reinforcing plate opposite to the upper reinforcing plate, and is used to rotatably mount the friction block assembly;

[0014] The second mounting component is fixed to the side of the rear reinforcing plate opposite to the front reinforcing plate and is used to rotatably mount the actuator cylinder assembly.

[0015] A support member is located within the box-shaped frame, and the edge of the support member is fixedly connected to the front reinforcing plate, the rear reinforcing plate, the upper reinforcing plate, and the lower reinforcing plate.

[0016] Furthermore, the tail skid system mounting device includes multiple support members, which are evenly divided into two groups. The upper reinforcing plate is a rectangular plate, and the front and rear reinforcing plates are both arc-shaped plates. The tops of the front and rear reinforcing plates are connected to the long side of the upper reinforcing plate at the same length. The second mounting member is located on the central axis of the rear reinforcing plate. The two groups of support members are symmetrically arranged in the box frame with the plane containing the central axis as the plane of symmetry. The second mounting member is connected to the rear reinforcing plate and the support members in sequence by bolts.

[0017] Furthermore, the support member includes a support plate and a plurality of reinforcing ribs, the plurality of reinforcing ribs being disposed on the same side of the support plate, the edge of the support plate being fixedly connected to the front reinforcing plate, the rear reinforcing plate, the upper reinforcing plate and the lower reinforcing plate, and the reinforcing ribs being arranged in a crisscross pattern to form a grid structure.

[0018] Furthermore, the friction block assembly includes two spaced-apart rotary joints, and the tail skid system mounting device includes two first mounting members. The two first mounting members are spaced apart along the width direction of the lower reinforcing plate. Each first mounting member includes a mounting plate and a first mounting lug. The mounting plate is fixedly connected to the lower reinforcing plate, and the first mounting lug is disposed on the mounting plate. The two rotary joints correspond one-to-one with the first mounting lugs of the two first mounting members and are rotatably connected by coaxially inserted pins.

[0019] Furthermore, the second mounting component includes a mounting base and two second mounting lugs. The mounting base is bolted to the rear reinforcing plate and the support member. The two second mounting lugs are spaced apart on the mounting base. The end of the actuating cylinder assembly is inserted between the two second mounting lugs and is rotatably connected by a coaxially inserted pin.

[0020] Furthermore, the lower reinforcing plate includes a mounting portion and an extension portion connected along the length direction. The width of the mounting portion is greater than the width of the extension portion. The front reinforcing plate, the rear reinforcing plate, and the first mounting member are all connected to the mounting portion. The extension portion and part of the mounting portion are attached and connected to the fuselage skin.

[0021] Furthermore, both the front reinforcing plate and the rear reinforcing plate are provided with weight-reducing holes.

[0022] Furthermore, the front reinforcing plate, the rear reinforcing plate, and the support member are all provided with through holes for cables or pipes to pass through.

[0023] Furthermore, the lower reinforcing plate is made of steel and has a thickness of 2-4 mm.

[0024] Furthermore, the upper reinforcing plate is connected to the front reinforcing plate, the rear reinforcing plate, and the fuselage skin, as well as the lower reinforcing plate is connected to the front reinforcing plate, the rear reinforcing plate, and the fuselage skin, and the front reinforcing plate and the rear reinforcing plate are connected to the fuselage skin via angle brackets.

[0025] The beneficial effects of this invention are:

[0026] The tail skid system mounting device proposed in this invention allows the friction block assembly to transfer the load to the box-shaped frame enclosed by the front, rear, upper, and lower reinforcing plates via a first mounting member connected to the lower reinforcing plate after being subjected to ground impact and friction load during tail skid system operation. The load borne by the actuator assembly is simultaneously transferred to the box-shaped frame via a second mounting member connected to the rear reinforcing plate. The support members inside the box-shaped frame are fixedly connected to the front, rear, upper, and lower reinforcing plates at their edges, further strengthening the overall integrity of the frame and forming a multi-directional load transfer path. This ensures that concentrated loads are no longer limited to a local area but are evenly distributed to the entire fuselage structure through the extensive connection between the box-shaped frame and the fuselage skin, preventing potential damage to the fuselage structure due to stress concentration. Furthermore, the rigid load-bearing system constructed by the box-shaped frame and the support members improves the load-bearing stability of the tail skid system, extends the service life of the first and second mounting members and the tail skid system itself, and more reliably ensures the structural safety and handling stability of the aircraft during minimum takeoff speed test flights. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the structure of the tail skid system installation device provided in an embodiment of the present invention;

[0028] Figure 2 This is a schematic diagram of the front reinforcing plate provided in an embodiment of the present invention;

[0029] Figure 3 This is a schematic diagram of the structure of the rear reinforcing plate provided in an embodiment of the present invention;

[0030] Figure 4 This is a schematic diagram of the upper reinforcing plate provided in an embodiment of the present invention;

[0031] Figure 5 This is a schematic diagram of the lower reinforcing plate provided in an embodiment of the present invention;

[0032] Figure 6 This is a schematic diagram of the structure of the first mounting component provided in an embodiment of the present invention;

[0033] Figure 7 This is a schematic diagram of the structure of the second mounting component provided in an embodiment of the present invention;

[0034] Figure 8 This is a structural schematic diagram of the support member provided in an embodiment of the present invention.

[0035] In the picture:

[0036] 1. Front reinforcement plate;

[0037] 2. Rear reinforcing plate;

[0038] 3. Install reinforcing plates;

[0039] 4. Lower reinforcing plate;

[0040] 5. First mounting component; 51. Mounting plate; 52. First mounting lug;

[0041] 6. Second mounting component; 61. Mounting base; 62. Second mounting lug;

[0042] 7. Supporting components; 71. Support plate; 72. Reinforcing ribs;

[0043] 8. Weight reduction hole;

[0044] 9. Through holes. Detailed Implementation

[0045] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, the accompanying drawings show only the parts relevant to the present invention, and not all of the structures.

[0046] In the description of this invention, unless otherwise explicitly specified and limited, the terms "connected," "linked," and "fixed" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0047] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0048] In the description of this embodiment, the terms "upper," "lower," "right," etc., refer to the orientation or positional relationship shown in the accompanying drawings. They are used only for ease of description and simplification of operation, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the present invention. In addition, the terms "first" and "second" are used only for distinction in description and have no special meaning.

[0049] The technical solution of the present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0050] See Figures 1-8 This invention provides a tail skid system mounting device for mounting a tail skid system to the bottom of the fuselage. The bottom of the fuselage has a mounting groove. The tail skid system includes a friction block assembly and an actuator assembly, the actuator assembly being able to drive the friction block assembly to rotate between a retracted position and a working position. The tail skid system mounting device includes a front reinforcing plate 1, a rear reinforcing plate 2, an upper reinforcing plate 3, a lower reinforcing plate 4, a first mounting component 5, a second mounting component 6, and a support component 7. The rear reinforcing plate 2 and the front reinforcing plate 1 are parallel and spaced apart along the length of the fuselage in the mounting groove and are both connected to the fuselage skin. The upper reinforcing plate 3 is located between the front reinforcing plate 1 and the rear reinforcing plate 2 and is connected to the top of both the front and rear reinforcing plates 1 and 2, and is also connected to the fuselage skin. The lower reinforcing plate 4 is attached to and connected to the fuselage skin. The bottoms of the front reinforcing plate 1 and the rear reinforcing plate 2 are both connected to... The lower reinforcing plate 4 is attached to the front reinforcing plate 1, rear reinforcing plate 2, upper reinforcing plate 3 and lower reinforcing plate 4 together form a box frame, which is located in the mounting groove; the first mounting member 5 is set on the side of the lower reinforcing plate 4 away from the upper reinforcing plate 3, and is used to rotatably install the friction block assembly; the second mounting member 6 is fixed on the side of the rear reinforcing plate 2 away from the front reinforcing plate 1, and is used to rotatably install the actuator cylinder assembly; the support member 7 is located in the box frame, and the edge of the support member 7 is fixedly connected to the front reinforcing plate 1, rear reinforcing plate 2, upper reinforcing plate 3 and lower reinforcing plate 4.

[0051] When the tail skid system is in operation, after the friction block assembly is subjected to ground impact and friction load, the load is transferred to the box frame enclosed by the front reinforcing plate 1, rear reinforcing plate 2, upper reinforcing plate 3, and lower reinforcing plate 4 through the first mounting piece 5 connected to the lower reinforcing plate 4. The load borne by the actuator assembly is simultaneously transferred to the box frame through the second mounting piece 6 connected to the rear reinforcing plate 2. The support piece 7 inside the box frame is fixedly connected to the front reinforcing plate 1, rear reinforcing plate 2, upper reinforcing plate 3, and lower reinforcing plate 4 at its edges, which further strengthens the overall integrity of the frame and forms a multi-directional load transfer path. This means that the concentrated load is no longer limited to a local area, but is evenly diffused to the entire fuselage structure through the extensive connection between the box frame and the fuselage skin. This avoids potential damage to the fuselage structure due to stress concentration. Furthermore, the rigid load-bearing system constructed by the box frame and the support piece 7 improves the load-bearing stability of the tail skid system, extends the service life of the first mounting piece 5, the second mounting piece 6, and the tail skid system itself, and more reliably ensures the structural safety and handling stability of the aircraft during minimum takeoff speed test flights.

[0052] Specifically, such as Figure 2 and Figure 3As shown, both the front reinforcing plate 1 and the rear reinforcing plate 2 have weight-reduction holes 8. As the core side load-bearing components of the box frame, the front reinforcing plate 1 and the rear reinforcing plate 2, while ensuring the structural strength meets the load transfer requirements, can effectively reduce the overall weight of the installation device and reduce the extra load on the aircraft by opening the weight-reduction holes 8.

[0053] Specifically, such as Figure 2 , Figure 3 and Figure 8 As shown, the front reinforcing plate 1, the rear reinforcing plate 2, and the support member 7 are all provided with through holes 9 for cables or pipes to pass through. The through holes 9 simplify the laying and maintenance process of cables and pipes and improve the convenience of installation and subsequent maintenance without affecting the load transfer balance and structural stability.

[0054] Specifically, the lower reinforcing plate 4 is made of steel and has a thickness of 2-4mm. Steel has excellent rigidity, impact resistance, and wear resistance. The 2-4mm thickness design ensures that the lower reinforcing plate 4 can stably bear the connecting force of the front reinforcing plate 1 and the rear reinforcing plate 2, as well as the ground contact load of the friction block assembly transmitted by the first mounting component 5, providing reliable bottom support for the box frame, while avoiding an increase in the overall weight of the mounting device due to excessive thickness.

[0055] Specifically, the upper reinforcing plate 3 is connected to the front reinforcing plate 1, the rear reinforcing plate 2, and the fuselage skin, as are the lower reinforcing plate 4 and the front reinforcing plate 1, the rear reinforcing plate 2, and the fuselage skin. The front reinforcing plate 1 and the rear reinforcing plate 2 are also connected to the fuselage skin via angle brackets. Angle brackets can increase the contact area between the components, disperse local stress at the connection points, and improve the strength and resistance to deformation of the connection.

[0056] In this embodiment, the front reinforcing plate 1, rear reinforcing plate 2, upper reinforcing plate 3, and support member 7 can all be made of aluminum alloy or titanium alloy. Aluminum alloy or titanium alloy has the excellent properties of being lightweight, high-strength, and corrosion-resistant. This can reduce the weight of the front reinforcing plate 1, rear reinforcing plate 2, upper reinforcing plate 3, and support member 7, reduce the overall load of the installation device, and improve the maneuverability of the aircraft during test flights. At the same time, it can ensure that the box-shaped frame enclosed by each reinforcing plate and the support member 7 have sufficient rigidity and impact resistance to stably bear the concentrated load transmitted by the tail skid system.

[0057] In this embodiment, when connecting angle brackets, the angle brackets are first attached to the joint of the components to be connected, such as the corner between the upper reinforcing plate 3 and the front reinforcing plate 1, and then bolts are sequentially inserted through the angle brackets and connecting components. The angle brackets can specifically be angle steel.

[0058] Specifically, such as Figure 5As shown, the lower reinforcing plate 4 includes a mounting portion 41 and an extension portion 42 connected along its length. The width of the mounting portion 41 is greater than the width of the extension portion 42. The front reinforcing plate 1, the rear reinforcing plate 2, and the first mounting member 5 are connected to the mounting portion 41. The extension portion 42 and part of the mounting portion 41 are fitted together and connected to the fuselage skin. The wider mounting portion 41 provides more sufficient connection space for the front reinforcing plate 1 and the rear reinforcing plate 2, ensuring the robustness of the box frame connection, while enhancing the load-bearing capacity of the first mounting member 5, allowing the load transmitted by the friction block assembly to be more stably transferred to the frame. The extension portion 42 is fitted together and connected to part of the mounting portion 41 and connected to the fuselage skin. The narrower extension portion 42 can precisely fit the bottom contour of the fuselage, further improving the fit between the mounting device and the aircraft shape and reducing air resistance.

[0059] Specifically, such as Figure 1 and Figure 6 As shown, the friction block assembly includes two spaced-apart rotary joints, and the tail skid system mounting device includes two first mounting members 5. The two first mounting members 5 are spaced apart along the width direction of the lower reinforcing plate 4. Each first mounting member 5 includes a mounting plate 51 and a first mounting lug 52. The mounting plate 51 is fixedly connected to the lower reinforcing plate 4, and the first mounting lug 52 is disposed on the mounting plate 51. The two rotary joints correspond one-to-one with the first mounting lugs 52 of the two first mounting members 5, and are rotatably connected by coaxial pins. The two spaced-apart rotary joints of the friction block assembly correspond one-to-one with the two spaced-apart first mounting members 5 on the lower reinforcing plate 4. The mounting plate 51 of each first mounting member 5 is firmly connected to the lower reinforcing plate 4, and the first mounting lug 52 is rotatably connected to the rotary joints through coaxial pins. This ensures that the friction block assembly can stably switch between the retracted and working positions, and through the symmetrical layout of the double joints and double first mounting members 5, the impact and friction load of the friction block assembly are evenly distributed to the two first mounting members 5, and then synchronously transmitted to the lower reinforcing plate 4 and the box frame.

[0060] In this embodiment, as Figure 6 As shown, each first mounting component 5 includes two first mounting lugs 52. The mounting plate 51 is rectangular, and the two mounting lugs 52 are spaced apart on the mounting plate 51 along its width. A rotatable joint is inserted between the two first mounting lugs 52 and forms a rotatable connection through a coaxially inserted pin to increase stability during rotation.

[0061] Specifically, such as Figure 1 and Figure 7As shown, the second mounting component 6 includes a mounting base 61 and two second mounting lugs 62. The mounting base 61 is bolted to the rear reinforcing plate 2 and the support member 7. The two second mounting lugs 62 are spaced apart on the mounting base 61. The end of the actuator assembly is inserted between the two second mounting lugs 62 and rotatably connected by a coaxially inserted pin. The mounting base 61 is directly fixed to the rear reinforcing plate 2, increasing the contact area with the rear reinforcing plate 2 through its own structure, thus distributing the load of the actuator assembly to the rear reinforcing plate 2 and avoiding localized stress concentration. The end of the actuator assembly is inserted between the two second mounting lugs 62 and rotatably connected by a coaxially inserted pin. This double-lug clamping structure not only evenly distributes the load of the actuator assembly to the rear reinforcing plate 2 and the box frame, but also simplifies installation.

[0062] More specifically, such as Figure 7 As shown, the mounting base 61 is stepped, and the two second mounting lugs 62 are located on the thicker step surface, which provides a stable load-bearing base for the lugs to enhance their impact resistance.

[0063] In this embodiment, both the first mounting ear 52 and the second mounting ear 62 are made of steel.

[0064] Specifically, such as Figure 1 and Figure 8 As shown, the tail skid system mounting device includes multiple support members 7, which are evenly divided into two groups. The upper reinforcing plate 3 is a rectangular plate, while the front reinforcing plate 1 and the rear reinforcing plate 2 are both arc-shaped plates. The tops of the front reinforcing plate 1 and the rear reinforcing plate 2 are connected to the long side of the upper reinforcing plate 3 at equal length. The second mounting member 6 is located on the central axis of the rear reinforcing plate 2. The two groups of support members 7 are symmetrically arranged within a box frame with the plane containing the central axis as the plane of symmetry. The second mounting member 6 is connected to the rear reinforcing plate 2 and the support members 7 in sequence by bolts. The arc-shaped bottom surfaces of the front reinforcing plate 1 and the rear reinforcing plate 2 are specially designed to fit the aircraft shape and conform to the bottom contour of the fuselage. Their top planes are connected to the long side of the rectangular upper reinforcing plate 3 at equal length, maximizing the contact area to ensure stable load transmission. Combined with the structure of the second mounting member 6 located on the central axis of the rear reinforcing plate 2 and the two groups of support members 7 symmetrically arranged, the concentrated load transmitted by the friction block assembly and the actuator cylinder assembly forms a more balanced transmission path that conforms to the fuselage structure, further reducing the risk of stress concentration and improving the load-bearing reliability and service life of the mounting device.

[0065] In this embodiment, as Figure 8 As shown, the tail skid system installation device includes two support members 7. The two support members 7 are symmetrically arranged in the box frame with the plane where the central axis of the reinforcing plate 2 is located as the plane of symmetry, and one of the support members 7 has a through hole 9.

[0066] In other embodiments, the tail skid system mounting device includes four support members 7, and the number of support members 7 is not specifically limited here.

[0067] More specifically, such as Figure 8 As shown, the support member 7 includes a support plate 71 and multiple reinforcing ribs 72. The multiple reinforcing ribs 72 are disposed on the same side of the support plate 71. The edge of the support plate 71 is fixedly connected to the front reinforcing plate 1, the rear reinforcing plate 2, the upper reinforcing plate 3, and the lower reinforcing plate 4. The reinforcing ribs 72 are arranged in a crisscross pattern to form a grid structure. The crisscross grid arrangement of the multiple reinforcing ribs 72 can significantly improve the structural rigidity and deformation resistance of the support plate 71 itself. It can also form a multi-node, multi-path load transfer channel through the grid structure. This allows the concentrated load transmitted by the tail skid system to be quickly dispersed to the four reinforcing plates through the grid-like reinforcing ribs 72 and the support plate 71 after being introduced into the box frame via the first mounting member 5 and the second mounting member 6. Then, it can be evenly diffused to the overall fuselage structure, further reducing the risk of local stress concentration.

[0068] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation of the present invention. Those skilled in the art will be able to make various obvious changes, readjustments, and substitutions without departing from the scope of protection of the present invention. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. A tail skid system mounting device for mounting a tail skid system to the bottom of a fuselage, wherein the bottom of the fuselage is provided with a mounting groove, the tail skid system comprising a friction block assembly and an actuator cylinder assembly, the actuator cylinder assembly being capable of driving the friction block assembly to rotate between a retracted position and a working position, characterized in that, The tail skid system mounting device includes: Front reinforcement plate (1); The rear reinforcing plate (2) and the front reinforcing plate (1) are arranged parallel to each other in the mounting groove along the length of the fuselage and are both connected to the fuselage skin. The upper reinforcing plate (3) is located between the front reinforcing plate (1) and the rear reinforcing plate (2) and is connected to the top of the front reinforcing plate (1) and the rear reinforcing plate (2), and the upper reinforcing plate (3) is connected to the fuselage skin; The lower reinforcing plate (4) is attached and connected to the fuselage skin. The bottom of the front reinforcing plate (1) and the rear reinforcing plate (2) are both connected to the lower reinforcing plate (4), so that the front reinforcing plate (1), the rear reinforcing plate (2), the upper reinforcing plate (3) and the lower reinforcing plate (4) together form a box frame, and the box frame is located in the mounting groove. The first mounting component (5) is disposed on the side of the lower reinforcing plate (4) away from the upper reinforcing plate (3) and is used to rotatably mount the friction block assembly; The second mounting component (6) is fixed to the side of the rear reinforcing plate (2) away from the front reinforcing plate (1) and is used to rotatably mount the actuator cylinder assembly; The support member (7) is located inside the box frame, and the edge of the support member (7) is fixedly connected to the front reinforcing plate (1), the rear reinforcing plate (2), the upper reinforcing plate (3) and the lower reinforcing plate (4); The support member (7) includes a support plate (71) and a plurality of reinforcing ribs (72). The plurality of reinforcing ribs (72) are disposed on the same side of the support plate (71). The edge of the support plate (71) is fixedly connected to the front reinforcing plate (1), the rear reinforcing plate (2), the upper reinforcing plate (3) and the lower reinforcing plate (4). The reinforcing ribs (72) are arranged in a crisscross pattern to form a grid structure. The lower reinforcing plate (4) includes a mounting portion (41) and an extension portion (42) connected along the length direction. The width of the mounting portion (41) is greater than the width of the extension portion (42). The front reinforcing plate (1), the rear reinforcing plate (2), and the first mounting member (5) are all connected to the mounting portion (41). The extension portion (42) and part of the mounting portion (41) are attached and connected to the fuselage skin. The upper reinforcing plate (3) is connected to the front reinforcing plate (1), the rear reinforcing plate (2) and the fuselage skin, and the lower reinforcing plate (4) is connected to the front reinforcing plate (1), the rear reinforcing plate (2) and the fuselage skin. The front reinforcing plate (1) and the rear reinforcing plate (2) are connected to the fuselage skin by angle brackets.

2. The tail skid system mounting device according to claim 1, characterized in that, The tail skid system mounting device includes multiple support members (7), which are divided into two groups. The upper reinforcing plate (3) is a rectangular plate, and the front reinforcing plate (1) and the rear reinforcing plate (2) are both arc-shaped plates. The tops of the front reinforcing plate (1) and the rear reinforcing plate (2) are connected to the long side of the upper reinforcing plate (3) at the same length. The second mounting member (6) is located on the central axis of the rear reinforcing plate (2). The two groups of support members (7) are symmetrically arranged in the box frame with the plane where the central axis is located as the plane of symmetry. The second mounting member (6) is connected to the rear reinforcing plate (2) and the support member (7) in sequence by bolts.

3. The tail skid system mounting device according to claim 1, characterized in that, The friction block assembly includes two spaced-apart rotary joints, and the tail skid system mounting device includes two first mounting parts (5). The two first mounting parts (5) are spaced apart along the width direction of the lower reinforcing plate (4). Each first mounting part (5) includes a mounting plate (51) and a first mounting lug (52). The mounting plate (51) is fixedly connected to the lower reinforcing plate (4), and the first mounting lug (52) is disposed on the mounting plate (51). The two rotary joints correspond one-to-one with the first mounting lugs (52) of the two first mounting parts (5) and are rotatedly connected by a coaxially inserted pin.

4. The tail skid system mounting device according to claim 1, characterized in that, The second mounting component (6) includes a mounting base (61) and two second mounting lugs (62). The mounting base (61) is bolted to the rear reinforcing plate (2) and the support member (7). The two second mounting lugs (62) are spaced apart on the mounting base (61). The end of the actuating cylinder assembly is inserted between the two second mounting lugs (62) and is rotatably connected by a coaxially inserted pin.

5. The tail skid system mounting device according to any one of claims 1-4, characterized in that, Both the front reinforcing plate (1) and the rear reinforcing plate (2) are provided with weight reduction holes (8).

6. The tail skid system mounting device according to any one of claims 1-4, characterized in that, The front reinforcing plate (1), the rear reinforcing plate (2), and the support member (7) are all provided with through holes (9) for cables or pipes to pass through.

7. The tail skid system mounting device according to any one of claims 1-4, characterized in that, The lower reinforcing plate (4) is made of steel and has a thickness of 2-4 mm.

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