Mounting device for tail skid system

Abstract

The invention 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, and the rear reinforcing plate and the front reinforcing plate are arranged in a mounting groove at an interval and are both connected with a fuselage skin; the upper reinforcing plate is located between the front reinforcing plate and the rear reinforcing plate, connected with the tops of the two and connected to the fuselage skin. The lower reinforcing plate is attached to and connected with the fuselage skin, the bottoms of the front reinforcing plate and the rear reinforcing plate are connected to the lower reinforcing plate, and a box type frame is defined by the front reinforcing plate, the rear reinforcing plate and the upper reinforcing plate. The first mounting piece is arranged on the lower reinforcing plate and used for rotationally mounting the friction block assembly; the second mounting piece is fixed on the rear reinforcing plate and is used for rotationally mounting the actuator cylinder assembly; the supporting piece is located in the box type frame and fixedly connected with the front reinforcing plate, the rear reinforcing plate, the upper reinforcing plate and the lower reinforcing plate. The problem of fuselage structure damage caused by load concentration can be solved, and therefore test flight safety is guaranteed.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of civil aviation engineering technology, and in particular to a tail skid system mounting device. BACKGROUND

[0002] Before being put into operation, a civil transport aircraft must complete a minimum ground speed flight test, and the minimum ground speed parameter of the aircraft under the critical state is determined through actual flight verification to ensure the flight safety and control stability of the aircraft during the take-off stage. When the minimum ground speed flight test is carried out, the tail of the aircraft is prone to contact and friction with the ground, thereby causing damage to the body structure of the aircraft.

[0003] To solve this problem, the existing technology generally adopts a protection scheme of installing a tail skid system on the lower surface of the aircraft. The tail skid system is mainly composed of a friction block assembly and an actuating cylinder assembly, and the installation position is usually selected at the tail skid contact point area of the rear fuselage web. The tail skid system utilizes the wear and tear of the friction block and the buffering effect of the actuating cylinder to reduce the impact of the ground impact on the fuselage.

[0004] However, although the existing tail skid system can absorb the ground impact and friction energy to some extent, there are still significant defects in actual application. Since the impact load and friction load generated when the aircraft touches the ground are instantaneous and high-strength, the existing tail skid system can only absorb the energy of its own components, but lacks an effective load transmission and diffusion mechanism. It is impossible to uniformly and efficiently diffuse the load concentrated on the tail skid system to the overall structure of the fuselage, resulting in excessive local load. Not only can it affect the service life of the tail skid system itself, but also can be transmitted to the body structure of the aircraft through the installation area, causing stress concentration of the structure, and then causing potential damage to 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

[0006] The purpose of the present application is to provide a tail skid system mounting device that can solve the problem of damage to the fuselage structure caused by load concentration in the prior art, thereby ensuring the safety of aircraft flight tests.

[0007] As conceived above, the technical solution adopted by the present application is:

[0008] The tail skid system mounting device is used to mount the tail skid system on the bottom of the fuselage, the bottom of the fuselage is provided with a mounting groove, the tail skid system includes a friction block assembly and an actuating cylinder assembly, the actuating cylinder assembly can drive the friction block assembly to rotate between a stowed position and a working position, and the tail skid system mounting device includes:

[0009] A front reinforcing plate;

[0010] A rear reinforcing plate is arranged in the mounting groove in parallel with the front reinforcing plate along the length direction of the fuselage and connected with the fuselage skin.

[0011] An upper reinforcing plate is arranged between the front reinforcing plate and the rear reinforcing plate and connected with the top of the front reinforcing plate and the rear reinforcing plate, and the upper reinforcing plate is connected with the fuselage skin.

[0012] A lower reinforcing plate is connected with the fuselage skin, and the bottom of the front reinforcing plate and the rear reinforcing plate is connected with the lower reinforcing plate, so that the front reinforcing plate, the rear reinforcing plate, the upper reinforcing plate and the lower reinforcing plate jointly form a box-shaped frame, and the box-shaped frame is arranged in the mounting groove.

[0013] A first mounting member is arranged on the side of the lower reinforcing plate away from the upper reinforcing plate, and is used for rotatably mounting the friction block assembly.

[0014] A second mounting member is fixed on the side of the rear reinforcing plate away from the front reinforcing plate, and is used for rotatably mounting the actuator cylinder assembly.

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

[0016] Further, the tail skid system mounting device comprises a plurality of support members, the plurality of support members are evenly divided into two groups, the upper reinforcing plate is a rectangular plate, the front reinforcing plate and the rear reinforcing plate are arc-shaped plates, the top of the front reinforcing plate and the top of the rear reinforcing plate are connected with the long side of the upper reinforcing plate, 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-shaped frame with the plane where the central axis is located as the symmetric plane, and the second mounting member is sequentially connected with the rear reinforcing plate and the support members through bolts.

[0017] Further, the support member comprises a support plate and a plurality of reinforcing ribs, the plurality of reinforcing ribs are arranged on the same side of the support plate, the edge of the support plate is fixedly connected with the front reinforcing plate, the rear reinforcing plate, the upper reinforcing plate and the lower reinforcing plate, and the reinforcing ribs are arranged in a longitudinal and transverse staggered manner to form a grid structure.

[0018] Further, the friction block assembly comprises two spaced rotary joints, the tail skid system mounting device comprises two first mounting members, the two first mounting members are spaced along the width direction of the lower reinforcing plate, each first mounting member comprises a mounting plate and a first mounting lug, the mounting plate is fixedly connected to the lower reinforcing plate, the first mounting lug is arranged on the mounting plate, the two rotary joints correspond to the first mounting lugs of the two first mounting members respectively, and the rotary joints are rotationally connected through coaxially arranged pin shafts.

[0019] Further, the second mounting member comprises a mounting seat and two second mounting lugs, the mounting seat is connected to the rear reinforcing plate and the support member through bolts, the two second mounting lugs are spaced on the mounting seat, the end of the actuator assembly is inserted between the two second mounting lugs, and the rotary connection is formed through coaxially arranged pin shafts.

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

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

[0022] Further, the front reinforcing plate, the rear reinforcing plate and the support member are all provided with through holes for cables or pipelines.

[0023] Further, the lower reinforcing plate is made of steel material, and the thickness is 2-4 mm.

[0024] Further, the upper reinforcing plate, the front reinforcing plate, the rear reinforcing plate and the fuselage skin, and the lower reinforcing plate, the front reinforcing plate, the rear reinforcing plate and the fuselage skin, and the front reinforcing plate and the rear reinforcing plate and the fuselage skin are all connected through angle bars.

[0025] The beneficial effects of the present application are as follows:

[0026] The tail skid system mounting device provided by the application, when the tail skid system works, the friction block assembly receives the load after being impacted by the ground and friction, and the load is transmitted to the box frame surrounded by the front reinforcing plate, the rear reinforcing plate, the upper reinforcing plate and the lower reinforcing plate through the first mounting part connected with the lower reinforcing plate; the load borne by the actuating cylinder assembly is synchronously transmitted to the box frame through the second mounting part connected with the rear reinforcing plate; the support part inside the box frame is fixedly connected with the front reinforcing plate, the rear reinforcing plate, the upper reinforcing plate and the lower reinforcing plate, which further strengthens the integrity of the frame, forms a multi-directional load transmission path, so that the concentrated load is no longer limited in a local area, but is evenly diffused to the whole structure of the fuselage through the extensive connection between the box frame and the fuselage skin, potential damage of the fuselage body structure caused by stress concentration is avoided, and the rigid bearing system formed by the box frame and the support part improves the bearing stability of the tail skid system, prolongs the service life of the first mounting part, the second mounting part and the tail skid system itself, and more reliably guarantees the safety of the aircraft structure and the steering stability during the minimum speed flight test. BRIEF DESCRIPTION OF DRAWINGS

[0027] Figure 1 FIG. 1 is a structural schematic diagram of a tail skid system mounting device provided by an embodiment of the application;

[0028] Figure 2 FIG. 2 is a structural schematic diagram of a front reinforcing plate provided by an embodiment of the application;

[0029] Figure 3 FIG. 3 is a structural schematic diagram of a rear reinforcing plate provided by an embodiment of the application;

[0030] Figure 4 FIG. 4 is a structural schematic diagram of an upper reinforcing plate provided by an embodiment of the application;

[0031] Figure 5 FIG. 5 is a structural schematic diagram of a lower reinforcing plate provided by an embodiment of the application;

[0032] Figure 6 FIG. 6 is a structural schematic diagram of a first mounting part provided by an embodiment of the application;

[0033] Figure 7 FIG. 7 is a structural schematic diagram of a second mounting part provided by an embodiment of the application;

[0034] Figure 8 FIG. 8 is a structural schematic diagram of a support part provided by an embodiment of the application.

[0035] In the drawings:

[0036] 1, front reinforcing plate;

[0037] 2, rear reinforcing plate;

[0038] 3, upper reinforcing plate;

[0039] 4. Lower reinforcing plate

[0040] 5. First mounting member; 51, mounting plate; 52, first mounting tab

[0041] 6. Second mounting member; 61, mounting seat; 62, second mounting tab

[0042] 7. Support member; 71, support plate; 72, reinforcing rib

[0043] 8. Weight-reducing hole

[0044] 9. Through hole DETAILED DESCRIPTION

[0045] The application will be further described below in conjunction with the drawings and embodiments. It should be understood that the specific embodiments described herein are merely intended for the purpose of interpretation of the present application and are not intended to limit the present application. In addition, it should be noted that only the parts related to the present application are shown in the drawings for the purpose of description, rather than all the structures.

[0046] In the description of the present application, unless otherwise explicitly specified and limited, the terms "connected", "connected", "fixed" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or it can be integrated; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the internal communication of two elements or the interaction relationship between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0047] In the present application, unless otherwise explicitly specified and limited, the "upper" or "lower" of the first feature to the second feature can include that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, the "upper", "above" and "on" of the first feature to the second feature includes that the first feature is directly above and obliquely above the second feature, or only indicates that the horizontal height of the first feature is higher than that of the second feature. The "below", "below" and "below" of the first feature to the second feature includes that the first feature is directly below and obliquely below the second feature, or only indicates that the horizontal height of the first feature is less than that of the second feature.

[0048] In the description of the present embodiment, the terms "upper", "lower", "right", and other orientation or position relationships are based on the orientation or position relationship shown in the drawings, and are only for the purpose of description and simplification of operation, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.

[0049] The technical solutions of the present application are further illustrated below in conjunction with the accompanying drawings and specific embodiments.

[0050] Referring to Figures 1-8 The present application provides 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, and the tail skid system comprises a friction block assembly and an actuating cylinder assembly, and the actuating cylinder assembly is capable of driving the friction block assembly to rotate between a stowed position and a working position. The tail skid system mounting device comprises a front reinforcing plate 1, a rear reinforcing plate 2, an upper reinforcing plate 3, a lower reinforcing plate 4, a first mounting member 5, a second mounting member 6 and a support member 7. The rear reinforcing plate 2 and the front reinforcing plate 1 are both arranged in parallel and spaced apart along the length direction 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 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 to and connected to the fuselage skin. The bottom of the front reinforcing plate 1 and the bottom of 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 enclose a box-type frame, and the box-type frame is located in the mounting groove. The first mounting member 5 is arranged on the side of the lower reinforcing plate 4 away from the upper reinforcing plate 3, and is used for rotatingly mounting the friction block assembly. The second mounting member 6 is fixed to the side of the rear reinforcing plate 2 away from the front reinforcing plate 1, and is used for rotatingly mounting the actuating cylinder assembly. The support member 7 is located in the box-type frame, and the edges of the support member 7 are fixedly connected to the front reinforcing plate 1, the rear reinforcing plate 2, the upper reinforcing plate 3 and the lower reinforcing plate 4.

[0051] When the tail skid system is working, after the friction block assembly is subjected to ground impact and friction load, the load is transmitted to the box-type frame enclosed by the front reinforcing plate 1, the rear reinforcing plate 2, the upper reinforcing plate 3 and the lower reinforcing plate 4 through the first mounting member 5 connected to the lower reinforcing plate 4. The load borne by the actuating cylinder assembly is synchronously transmitted to the box-type frame through the second mounting member 6 connected to the rear reinforcing plate 2. The support member 7 inside the box-type frame is fixedly connected to the edges of the front reinforcing plate 1, the rear reinforcing plate 2, the upper reinforcing plate 3 and the lower reinforcing plate 4, thereby further strengthening the overall integrity of the frame, forming a multi-directional load transmission path, so that the concentrated load is no longer limited to a local area, but is evenly diffused to the overall structure of the fuselage through the extensive connection of the box-type frame and the fuselage skin, thereby avoiding potential damage to the body structure of the fuselage due to stress concentration, and the rigid bearing system formed by the box-type frame and the support member 7 improves the bearing stability of the tail skid system, prolongs the service life of the first mounting member 5, the second mounting member 6 and the tail skid system itself, and more reliably guarantees the safety of the aircraft structure and the stability of the aircraft control during the minimum speed flight test.

[0052] Specifically, as Figure 2 and Figure 3As shown, the front reinforcing plate 1 and the rear reinforcing plate 2 are both provided with a weight-reducing hole 8. The front reinforcing plate 1 and the rear reinforcing plate 2 are core side bearing components of the box frame. On the premise that the structural strength meets the load transmission requirement, the weight-reducing hole 8 can effectively reduce the overall weight of the installation device and reduce the additional weight of the aircraft.

[0053] Specifically, as shown in Figure 2 、 Figure 3 and Figure 8 , the front reinforcing plate 1, the rear reinforcing plate 2 and the support 7 are all provided with a through hole 9 for cable or pipeline passing. The through hole 9 does not affect the load transmission balance and structural stability, simplifies the laying and maintenance process of the cable and pipeline, and improves the convenience of installation and later maintenance.

[0054] Specifically, the lower reinforcing plate 4 is made of steel material and has a thickness of 2-4 mm. The steel material has excellent rigidity, impact resistance and wear resistance. The thickness of 2-4 mm can ensure that the lower reinforcing plate 4 can stably bear the connecting force of the front reinforcing plate 1 and the rear reinforcing plate 2 and the friction block assembly ground load transmitted by the first mounting 5, and provide reliable bottom support for the box frame, and avoid increasing the overall weight of the installation device due to excessive thickness.

[0055] Specifically, the upper reinforcing plate 3, the front reinforcing plate 1, the rear reinforcing plate 2 and the fuselage skin, and the lower reinforcing plate 4, the front reinforcing plate 1, the rear reinforcing plate 2 and the fuselage skin, and the front reinforcing plate 1 and the rear reinforcing plate 2 and the fuselage skin are all connected by angle bars. The angle bar can increase the connection contact area between the components, disperse the local stress of the connection point, and improve the firmness and anti-deformation ability of the connection.

[0056] In this embodiment, the front reinforcing plate 1, the rear reinforcing plate 2, the upper reinforcing plate 3 and the support 7 can be made of aluminum alloy or titanium alloy. Aluminum alloy or titanium alloy has excellent characteristics of light weight, high strength and corrosion resistance. It can not only reduce the weight of the front reinforcing plate 1, the rear reinforcing plate 2, the upper reinforcing plate 3 and the support 7, reduce the overall weight of the installation device, and improve the maneuvering flexibility of the aircraft during test flight, but also ensure that the box frame surrounded by the reinforcing plates and the support 7 have sufficient rigidity and impact resistance to stably bear the concentrated load transmitted by the tail skid system.

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

[0058] Specifically, as shown in Figure 5As shown, 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 that 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, and the extension portion 42 is attached to and connected to the fuselage skin together with part of the mounting portion 41. The wider mounting portion 41 can provide more sufficient connection space for the front reinforcing plate 1 and the rear reinforcing plate 2, ensure the firmness of the box-shaped frame connection, and at the same time enhance the bearing support capacity of the first mounting member 5, so that the load transmitted by the friction block assembly is more stably introduced into the frame; the extension portion 42 is attached to and connected to the fuselage skin together with part of the mounting portion 41, and the narrower extension portion 42 can accurately fit the contour of the bottom of the fuselage, further improving the fit of the mounting device with the aircraft shape and reducing air resistance.

[0059] Specifically, as shown in Figure 1 and Figure 6 , the friction block assembly includes two spaced-apart rotary joints, and the ski 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 arranged on the mounting plate 51, the two rotary joints correspond one-to-one to the first mounting lugs 52 of the two first mounting members 5 and are rotationally connected by a coaxially arranged pin shaft. The two spaced-apart rotary joints of the friction block assembly correspond one-to-one to the two first mounting members 5 spaced apart along the width direction 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 rotationally connected to the rotary joint by a coaxial pin shaft, which not only ensures that the friction block assembly can stably switch between the stowed and working positions, but also uniformly disperses the ground impact and friction load of the friction block assembly to the two first mounting members 5 through the symmetrical layout of the double joints and double first mounting members 5, and then synchronously transmits them to the lower reinforcing plate 4 and the box-shaped frame.

[0060] In the present embodiment, as shown in Figure 6 , each first mounting member 5 includes two first mounting lugs 52, the mounting plate 51 is rectangular, the two mounting lugs 52 are spaced apart along the width direction of the mounting plate 51 and arranged on the mounting plate 51, and the rotary joint is inserted between the two first mounting lugs 52 and rotationally connected by a coaxially arranged pin shaft. To increase the stability during rotation.

[0061] Specifically, as shown in Figure 1 and Figure 7As shown, the second mounting member 6 includes a mounting seat 61 and two second mounting lugs 62, the mounting seat 61 is bolted to the rear reinforcing plate 2 and the support member 7, the two second mounting lugs 62 are arranged on the mounting seat 61 in a spaced manner, the end of the actuator cylinder assembly is inserted between the two second mounting lugs 62, and the rotation connection is formed through the coaxially arranged pin shaft. The mounting seat 61 is directly fixedly connected to the rear reinforcing plate 2, the contact area with the rear reinforcing plate 2 is increased through the structure itself, the load of the actuator cylinder assembly is dispersedly transmitted to the rear reinforcing plate 2, and local stress concentration is avoided. The end of the actuator cylinder assembly is inserted between the two second mounting lugs 62, and the rotation connection is formed through the coaxially arranged pin shaft. This double-lug clamping structure not only can evenly transmit the load of the actuator cylinder assembly to the rear reinforcing plate 2 and the box frame, but also is simple to install.

[0062] More specifically, as shown in Figure 7 The mounting seat 61 is in a stepped shape, and the two second mounting lugs 62 are arranged at the thicker step surface, which provides a stable bearing basis for the lugs to enhance the impact resistance.

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

[0064] Specifically, as shown in Figure 1 and Figure 8 The tail skid system mounting device includes a plurality of support members 7, the plurality of support members 7 are evenly divided into two groups, the upper reinforcing plate 3 is a rectangular plate, the front reinforcing plate 1 and the rear reinforcing plate 2 are both arc-shaped plates, the top of the front reinforcing plate 1 and the top of the rear reinforcing plate 2 are both connected to the long side of the upper reinforcing plate 3, 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 symmetry plane, and the second mounting member 6 is sequentially connected to the rear reinforcing plate 2 and the support member 7 through bolts. The arc-shaped bottom surfaces of the front reinforcing plate 1 and the rear reinforcing plate 2 are specially designed to match the outer shape of the aircraft, and can be matched with the contour of the bottom of the fuselage; the top planes of the front reinforcing plate 1 and the rear reinforcing plate 2 are connected to the long side of the rectangular upper reinforcing plate 3, the maximum contact area is used to ensure stable transmission of load, and the structure that the second mounting member 6 is arranged on the central axis of the rear reinforcing plate 2 and the two groups of support members 7 are symmetrically arranged, makes the concentrated load transmitted by the friction block assembly and the actuator cylinder assembly form a more matched balanced transmission path of the fuselage structure, further reduces the risk of stress concentration, and improves the load-bearing reliability and service life of the mounting device.

[0065] In this embodiment, as shown in Figure 8 The tail skid system mounting 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 symmetry plane, and a through hole 9 is formed in one of the support members 7.

[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 herein.

[0067] More specifically, as shown in Figure 8 The support member 7 includes a support plate 71 and a plurality of reinforcing ribs 72 arranged on the same side of the support plate 71, and the edges of the support plate 71 are fixedly connected with 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 longitudinal and transverse staggered manner to form a grid structure. The plurality of reinforcing ribs 72 are arranged in a longitudinal and transverse staggered grid manner, which can greatly improve the structural rigidity and deformation resistance of the support plate 71, and also form a multi-node and multi-path load transmission channel through the grid structure. After the concentrated load transmitted by the tail skid system is introduced into the box frame through the first mounting member 5 and the second mounting member 6, the concentrated load can be quickly dispersed to the four reinforcing plates through the grid-shaped reinforcing ribs 72 and the support plate 71, and then evenly spread to the overall structure of the fuselage, further reducing the risk of local stress concentration.

[0068] Obviously, the above embodiments of the present application are only examples for clear illustration of the present application, and are not intended to limit the embodiments of the present application. Those skilled in the art can make various obvious changes, readjustments and substitutions without departing from the scope of the present application. It is not necessary and impossible to exhaust all the embodiments. Any modification, equivalent substitution and improvement within the spirit and principle of the present application shall be included in the protection scope of the claims of the present application.

Claims

1. A tail skid system mounting device for mounting a tail skid system to a bottom of a fuselage, the bottom of the fuselage being provided with a mounting slot, the tail skid system comprising a friction block assembly and an actuating cylinder assembly, the actuating cylinder assembly being capable of driving the friction block assembly to rotate between a stowed position and a working position, characterised in that, The tail skid system mounting device comprises: a front reinforcing plate (1); a rear reinforcing plate (2), which is arranged in the mounting groove in parallel with the front reinforcing plate (1) along the length direction of the fuselage and connected with the fuselage skin; an upper reinforcing plate (3), which is located between the front reinforcing plate (1) and the rear reinforcing plate (2) and connected with the top of the front reinforcing plate (1) and the rear reinforcing plate (2), and connected with the fuselage skin; a lower reinforcing plate (4), which is connected with the fuselage skin, and the bottom of the front reinforcing plate (1) and the rear reinforcing plate (2) is connected with 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-shaped frame, which is located in the mounting groove; a first mounting part (5), which is arranged on the side of the lower reinforcing plate (4) away from the upper reinforcing plate (3) and used for rotatingly mounting the friction block assembly; a second mounting part (6), which is fixed on the side of the rear reinforcing plate (2) away from the front reinforcing plate (1) and used for rotatingly mounting the actuator cylinder assembly; a support part (7), which is located in the box-shaped frame and the edge of the support part (7) is fixedly connected with the front reinforcing plate (1), the rear reinforcing plate (2), the upper reinforcing plate (3) and the lower reinforcing plate (4).

2. The sled system mounting arrangement of claim 1, wherein, The tail skid system mounting device comprises a plurality of support parts (7), the plurality of support parts (7) are averagely divided into two groups, the upper reinforcing plate (3) is a rectangular plate, the front reinforcing plate (1) and the rear reinforcing plate (2) are arc-shaped plates, the top of the front reinforcing plate (1) and the rear reinforcing plate (2) is connected with the long side of the upper reinforcing plate (3), the second mounting part (6) is located on the central axis of the rear reinforcing plate (2), the two groups of support parts (7) are symmetrically arranged in the box-shaped frame with the plane where the central axis is located as the symmetric plane, and the second mounting part (6) is connected with the rear reinforcing plate (2) and the support part (7) in sequence through bolts.

3. The sled system mounting arrangement of claim 2, wherein, The support part (7) comprises a support plate (71) and a plurality of reinforcing ribs (72), the plurality of reinforcing ribs (72) are arranged on the same side of the support plate (71), the edge of the support plate (71) is fixedly connected with the front reinforcing plate (1), the rear reinforcing plate (2), the upper reinforcing plate (3) and the lower reinforcing plate (4), and the reinforcing ribs (72) are arranged in a longitudinal and transverse staggered manner to form a grid structure.

4. The sled system mounting arrangement of claim 1, wherein The friction block assembly comprises two spaced rotary joints, the tail skid system mounting device comprises two first mounting members (5), the two first mounting members (5) are spaced along the width direction of the lower reinforcing plate (4), each first mounting member (5) comprises a mounting plate (51) and a first mounting lug (52), the mounting plate (51) is fixedly connected to the lower reinforcing plate (4), the first mounting lug (52) is arranged on the mounting plate (51), and the two rotary joints are in one-to-one correspondence with the first mounting lugs (52) of the two first mounting members (5) and are rotationally connected through coaxially arranged pin shafts.

5. The sled system mounting arrangement of claim 1, wherein The second mounting member (6) comprises a mounting seat (61) and two second mounting lugs (62), the mounting seat (61) is connected to the rear reinforcing plate (2) and the support member (7) through bolts, and the two second mounting lugs (62) are spaced on the mounting seat (61), the end of the actuator assembly is inserted between the two second mounting lugs (62), and the two second mounting lugs (62) are rotationally connected through coaxially arranged pin shafts.

6. The sled system mounting arrangement of claim 1, wherein The lower reinforcing plate (4) comprises a mounting portion (41) and an extension portion (42) connected along the length direction, the width of the mounting portion (41) is greater than that 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), and the extension portion (42) and part of the mounting portion (41) are attached and connected to the fuselage skin.

7. The sled system mounting arrangement of any of claims 1-6, wherein, The front reinforcing plate (1) and the rear reinforcing plate (2) are provided with weight reduction holes (8).

8. The sled system mounting arrangement of any of claims 1-6, wherein, The front reinforcing plate (1), the rear reinforcing plate (2) and the support member (7) are provided with through holes (9) for cables or pipelines to pass through.

9. The sled system mounting arrangement of any of claims 1-6, wherein, The lower reinforcing plate (4) is made of steel material and has a thickness of 2-4 mm.

10. The sled system mounting arrangement of any of claims 1-6, wherein, The upper reinforcing plate (3), the front reinforcing plate (1), the rear reinforcing plate (2) and the fuselage skin, and the lower reinforcing plate (4), the front reinforcing plate (1), the rear reinforcing plate (2) and the fuselage skin, and the front reinforcing plate (1) and the rear reinforcing plate (2) and the fuselage skin are all connected through angle bars.

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