Fixing device for actuator connector of undercarriage and aircraft structure

Abstract

The invention relates to the technical field of aircraft fuselage structures, in particular to a fixing device for an actuator connector of an undercarriage and an aircraft structure. Wherein the upper side of the first fixing piece is connected with a floor beam of an airplane, the lower side is connected with a stringer at the bottom of the airplane, and the upper side of the second fixing piece is connected with the floor beam of the airplane, and the lower side is connected with another stringer at the bottom of the airplane. The actuator connector can transmit the borne load to the floor beam and the stringer at the bottom of the aircraft through the first fixing piece and the second fixing piece, and therefore the load borne by the actuator connector is dispersed to the floor beam and the stringer which are fixed to the aircraft body. Loads borne by the first fixing piece and the second fixing piece can be transmitted mutually through the transition piece, and the flight safety of the aircraft is improved. According to the aircraft structure, the fixing device is arranged, so that the stress concentration phenomenon at the mounting position of the actuator connector can be relieved, and the flight safety of an aircraft is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft fuselage structure, and particularly relates to a fixing device for actuator joint of landing gear and an aircraft structure. BACKGROUND

[0002] The actuator of the aircraft landing gear is movably connected with the aircraft landing gear, and is used for pulling up or releasing the landing gear. The actuator is generally connected with an actuator joint, and the actuator joint is installed on the aircraft fuselage. When the actuator is in action, a reaction force is generated on the actuator joint, and thus stress concentration phenomenon will occur at the installation position of the actuator joint. With the increase of the use times of the landing gear, the actuator joint will even be loose or fall off, which seriously affects the flight safety. In addition, since the actuator needs to be supported firmly, it is usually necessary to select the existing structures such as the fuselage wall plate and frame, which leads to the limitation of the arrangement position of the actuator. If the actuator is not arranged on these existing structures, it is difficult to effectively transmit the load of the actuator joint. In addition, the landing gear compartment of the fuselage needs to be effectively closed around to prevent the external airflow, sand and the like from entering the interior of the fuselage.

[0003] In the prior art, the actuator joint is generally installed on a fixing member, the fixing member is connected with the aircraft wall plate, and the reaction force received by the actuator joint can be transmitted to the aircraft wall plate, so as to reduce the stress concentration phenomenon at the installation position of the actuator joint. However, the transmission of the reaction force to the aircraft wall plate cannot greatly reduce the stress concentration phenomenon, and the actuator joint will still have the risk of loosening or falling off over a long period of time, thereby affecting the flight safety. Therefore, it is urgent to propose a scheme to solve the above problems. SUMMARY

[0004] The first object of the present application is to provide a fixing device for actuator joint of landing gear, so as to solve the problem of serious stress concentration phenomenon at the installation position of the actuator joint in the prior art, which affects the flight safety.

[0005] The second object of the present application is to provide an aircraft structure, so as to solve the problem of serious stress concentration phenomenon at the installation position of the actuator joint in the prior art, which affects the flight safety.

[0006] According to the above idea, the technical scheme adopted by the present application is as follows:

[0007] The application discloses a fixing device for an actuator joint of an undercarriage, which comprises oppositely arranged first and second fixing members, wherein the upper side of the first fixing member is used for connecting a floor beam of an airplane, and the lower side of the first fixing member is used for connecting a longeron of the bottom of the airplane; the upper side of the second fixing member is used for connecting a floor beam of an airplane, and the lower side of the second fixing member is used for connecting another longeron of the bottom of the airplane; the side of the first fixing member and the side of the second fixing member, which are away from each other, are used for mounting the actuator joint; and the fixing device further comprises a transition member connected between the first and second fixing members.

[0008] Optionally, the fixing device further comprises two top fixing members, which are capable of being connected between two adjacent floor beams, and one side of one of the top fixing members is connected to the upper side of the first fixing member, and the other side of the top fixing member is used for connecting a wall plate of the airplane; and one side of the other top fixing member is connected to the upper side of the second fixing member, and the other side of the other top fixing member is used for connecting a wall plate of the airplane.

[0009] Optionally, the fixing device further comprises side fixing members, which are capable of being connected between the floor beam and the frame of the fuselage, and the side fixing members are connected to one side or both sides of the first fixing member along the length direction of the airplane, and the side fixing members are connected to one side or both sides of the second fixing member along the length direction of the airplane.

[0010] Optionally, the fixing device further comprises a third fixing member, which is connected to one side of the first fixing member along the length direction of the airplane and one side of the second fixing member along the length direction of the airplane, and the lower side of the third fixing member is used for connecting the frame of the fuselage.

[0011] Optionally, the third fixing member is in the form of a plate, and the thickness direction of the third fixing member is parallel to the length direction of the airplane.

[0012] Optionally, the first and second fixing members are both in the form of a plate, and the thickness direction of the first and second fixing members is parallel to the width direction of the airplane.

[0013] Optionally, reinforcing ribs are arranged on the first and second fixing members.

[0014] Optionally, the transition member is in the form of a strip, and the two ends of the transition member along the length direction of the transition member are connected to the first and second fixing members respectively.

[0015] Optionally, the cross section of the transition member is in the form of U or I.

[0016] An airplane structure, which comprises the fixing device.

[0017] The application has the following beneficial effects:

[0018] The application provides a fixing device for an actuator joint of a landing gear, which comprises oppositely arranged first and second fixing members, the upper side of the first fixing member is used for connecting a floor beam of an airplane, and the lower side is used for connecting a longeron at the bottom of the airplane, the upper side of the second fixing member is used for connecting the floor beam of the airplane, and the lower side is used for connecting another longeron at the bottom of the airplane, the side away from each other of the first and second fixing members is used for mounting the actuator joint, and the fixing device further comprises a transition member connected between the first and second fixing members; when the actuator joint bears the load brought by the actuator, the actuator joint can transmit the load borne to the floor beam and the longerons at the bottom of the airplane through the first and second fixing members due to the connection of the first and second fixing members with the floor beam and the two longerons at the bottom of the airplane, thereby dispersing the load borne by the actuator joint to the floor beam and the longerons inherent to the fuselage, reducing the stress concentration phenomenon at the mounting position of the actuator joint, and in addition, the load borne by the first and second fixing members can be transmitted to each other through the transition member, thereby further dispersing the load borne by any actuator joint, and improving the flight safety of the airplane.

[0019] The application provides an airplane structure, which can disperse the load borne by the actuator joint to the floor beam and the longerons inherent to the fuselage through the fixing device, the load borne by the first and second fixing members can be transmitted to each other through the transition member, thereby reducing the stress concentration phenomenon at the mounting position of the actuator joint, and improving the flight safety of the airplane. BRIEF DESCRIPTION OF DRAWINGS

[0020] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the description of the embodiments of the present application will be briefly introduced. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative effort on the basis of the contents of the embodiments of the present application and the drawings.

[0021] Fig. 1 is a structural schematic view of a fixing device provided by the embodiments of the present application;

[0022] Fig. 2 is a structural schematic view of the connection between the fixing device and the fuselage structure provided by the embodiments of the present application.

[0023] In the drawings:

[0024] 100, floor beam; 200, longeron; 300, wall plate; 400, fuselage frame; 500, actuator joint; 600, wing beam;

[0025] 1, first fixing member; 2, second fixing member; 3, top fixing member; 4, side fixing member; 5, transition member; 6, third fixing member; 7, extension member. DETAILED DESCRIPTION

[0026] In order to make the technical problems solved by the present application, the technical solutions adopted and the technical effects reached more clear, the technical solutions of the present application will be further described below in conjunction with the accompanying drawings and specific embodiments. It can be understood that the specific embodiments described here are only used to explain the present application, but not limit the present application. In addition, it should be noted that, for the convenience of description, only the parts related to the present application are shown in the drawings, not all.

[0027] It should be noted that: similar reference numerals and letters represent similar items in the following drawings, therefore, once an item is defined in one drawing, it does not need to be further defined and explained in the subsequent drawings.

[0028] 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 fixed connection, or detachable connection, or integrated; it can be mechanical connection, or electrical connection; it can be directly connected, or indirectly connected through intermediate media, 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.

[0029] In the present application, unless otherwise explicitly specified and limited, the "upper" or "lower" of the first feature to the second feature can include the direct contact of the first and second features, or can include the contact of the first and second features through another feature between them. Moreover, the "upper", "upper" and "upper" of the first feature to the second feature includes the vertical direction of the first feature above and oblique above the second feature, or only indicates that the horizontal height of the first feature is higher than that of the second feature. The "lower", "lower" and "lower" of the first feature to the second feature includes the vertical direction of the first feature below and oblique below the second feature, or only indicates that the horizontal height of the first feature is less than that of the second feature. In the description of the present embodiment, if not specially stated, "a plurality of" specifically refers to two or more than two.

[0030] In the description of the present embodiment, the terms "upper", "lower", "right", etc. orientation or position relationship is based on the orientation or position relationship shown in the drawings, only for the convenience of description and simplification of operation, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, therefore, it cannot be understood as a limitation on the present application. In addition, the terms "first", "second" are only used to distinguish in the description, and have no special meaning.

[0031] It should be noted that when an element is referred to as being "fixed to" or "set on" another element, it can be directly on the other element or there can be an intervening element.

[0032] The technical solutions of the present application will be further illustrated below in conjunction with the accompanying drawings and specific embodiments.

[0033] The present embodiment provides a fixing device for an actuator joint of a landing gear and an aircraft structure, which is used to solve the problem of stress concentration at the installation position of the actuator joint in the prior art, which affects flight safety.

[0034] As shown in Figs. 1-2 The fixing device comprises oppositely arranged first and second fixing members 1 and 2. The upper side of the first fixing member 1 is used to connect a floor beam 100 of the aircraft, and the lower side is used to connect a longeron 200 at the bottom of the aircraft. The upper side of the second fixing member 2 is used to connect the floor beam 100 of the aircraft, and the lower side is used to connect another longeron 200 at the bottom of the aircraft. The side of the first fixing member 1 and the second fixing member 2 away from each other is used to install the actuator joint 500. The fixing device further comprises a transition member 5 connected between the first and second fixing members 1 and 2.

[0035] Understandably, the lifting and lowering of the aircraft landing gear is generally achieved by the landing gear actuator. The landing gear actuator is movably connected to the landing gear at one end and movably connected to the actuator joint 500 at the other end, and the actuator joint 500 is installed on the fuselage. When the actuator is actuated, the landing gear can be lifted or released, and at the same time the actuator will generate a reaction force on the actuator joint 500, so that stress concentration will occur at the installation position of the actuator joint 500, and with the increase of the use frequency of the landing gear, the actuator joint 500 will even loosen or fall off, which seriously affects the flight safety. In the embodiment, by installing the fixing device on the aircraft, the first fixing member 1 and the second fixing member 2 of the fixing device are connected to the floor beam 100 and the longeron 200 of the aircraft, and the actuator joint 500 is installed on the first fixing member 1 and the second fixing member 2. When the actuator is actuated, the reaction force borne by the actuator joint 500 is first transmitted to the first fixing member 1 and the second fixing member 2, and then transmitted to the floor beam 100 and the longeron 200 through the first fixing member 1 and the second fixing member 2. That is, by providing the first fixing member 1 and the second fixing member 2, the load borne by the actuator joint 500 is dispersed to the inherent floor beam 100 and longeron 200 of the fuselage. Further, by providing the transition piece 5, the load borne by the first fixing member 1 and the second fixing member 2 can be transmitted to each other through the transition piece 5, balancing the load borne by the first fixing member 1 and the second fixing member 2. Finally, through the first fixing member 1, the second fixing member 2 and the transition piece 5 connected between the first fixing member 1 and the second fixing member 2, the load borne by the actuator joint 500 is effectively dispersed, avoiding stress concentration and greatly improving the flight safety of the aircraft.

[0036] Optionally, the first fixing member 1 and the second fixing member 2 are both plate-shaped, and the thickness direction of the first fixing member 1 and the second fixing member 2 is parallel to the width direction of the aircraft. This setting can save the internal space of the fuselage, improve the space utilization rate of the aircraft, and the thickness direction of the first fixing member 1 and the second fixing member 2 parallel to the width direction of the aircraft can facilitate the installation of the actuator joint 500 and improve the overall structural rationality.

[0037] In order to improve the structural strength of the first fixing member 1 and the second fixing member 2, optionally, reinforcing ribs are provided on the first fixing member 1 and the second fixing member 2. This setting can avoid damage to the first fixing member 1 and the second fixing member 2, thereby improving the use reliability of the fixing device and improving user satisfaction.

[0038] Exemplarily, the side of the first fixing member 1 and the second fixing member 2 close to each other is provided with reinforcing ribs, and the reinforcing ribs are net-shaped, including intersecting horizontal ribs and vertical ribs. This setting further improves the structural strength of the first fixing member 1 and the second fixing member 2, and can facilitate the installation of the actuator joint 500 and avoid position interference between the actuator joint 500 and the reinforcing ribs.

[0039] Optionally, an extension member 7 is connected between the lower side of the first fixing member 1 and one of the longerons 200, and another extension member 7 is connected between the lower side of the second fixing member 2 and another of the longerons 200. This arrangement can make a transition through the extension members 7 when the first fixing member 1 and the second fixing member 2 do not correspond to the positions of the longerons 200, thereby improving the flexibility of the fixing device.

[0040] Illustratively, the radial cross section of the extension member 7 is in the shape of a fan ring. This arrangement can make the extension member 7 adapt to the shape of the longeron 200, thereby improving the adaptability of the fixing device.

[0041] In other embodiments, the extension member 7 can also have other shapes, which can be set as needed according to the aircraft model, and are not limited here.

[0042] Optionally, the fixing device further comprises two top fixing members 3, which can be connected between two adjacent floor beams 100, and one of the top fixing members 3 is connected to the upper side of the first fixing member 1 and the other side is used to connect the wall panel 300 of the aircraft, and the other of the top fixing members 3 is connected to the upper side of the second fixing member 2 and the other side is used to connect the wall panel 300 of the aircraft.

[0043] As can be understood, the top fixing member 3 can be connected between two adjacent floor beams 100, and the top fixing member 3 is connected to the upper side of the first fixing member 1 and the upper side of the second fixing member 2, so that the top fixing member 3 can improve the efficiency of the first fixing member 1 and the second fixing member 2 in transmitting loads to the floor beams 100, and can improve the structural strength of the first fixing member 1 and the second fixing member 2, thereby improving the service life. In addition, the top fixing member 3 can transmit the load borne by the first fixing member 1 and the second fixing member 2 to the wall panel 300, further dispersing the load, thereby improving the reliability of the fixing device.

[0044] Illustratively, the top fixing member 3 is in the shape of a plate, and the thickness direction of the top fixing member 3 is horizontally perpendicular to the length direction of the aircraft, and the top surface of one of the top fixing members 3 is fitted and mounted to the bottom surface of the floor beam 100 with the edges on the opposite sides, and one end abuts the wall panel 300, and the edge on one side of the bottom surface is connected perpendicularly to the first fixing member 1; and the top surface of the other of the top fixing members 3 is fitted and mounted to the bottom surface of the floor beam 100 with the edges on the opposite sides, and one end abuts the wall panel 300, and the edge on one side of the bottom surface is connected perpendicularly to the second fixing member 2. This arrangement saves the internal space of the fuselage, reduces the overall weight of the aircraft, and improves the contact area of the top fixing member 3 with the floor beam 100, the wall panel 300, and the first fixing member 1 and the second fixing member 2, thereby improving the load transmission efficiency.

[0045] Optionally, the fixing device further comprises side fixing members 4, which are connectable between the floor beam 100 and the fuselage frame 400, and the first fixing member 1 is connected with the side fixing members 4 on one side or both sides in the length direction of the aircraft, and the second fixing member 2 is also connected with the side fixing members 4 on one side or both sides in the length direction of the aircraft. This arrangement can improve the efficiency of the first fixing member 1 and the second fixing member 2 in transferring loads to the floor beam 100, and can improve the structural strength of the first fixing member 1 and the second fixing member 2 to a certain extent, while the side fixing members 4 can transfer the loads borne by the first fixing member 1 and the second fixing member 2 to the fuselage frame 400, further dispersing the loads and improving the use reliability of the fixing device.

[0046] Exemplarily, the side fixing members 4 are provided in four and are in the form of plates, the thickness direction of the side fixing members 4 is parallel to the length direction of the aircraft, the top edge of one side surface of the side fixing members 4 is fitted and installed on the side surface of the floor beam 100, and one side edge of the side fixing members 4 is connected to the fuselage frame 400; in the length direction of the aircraft, one side of the first fixing member 1 is perpendicularly connected to one side surface of one side fixing member 4, the other side of the first fixing member 1 is perpendicularly connected to one side surface of another side fixing member 4, one side of the second fixing member 2 is perpendicularly connected to one side surface of another side fixing member 4, and the other side of the second fixing member 2 is perpendicularly connected to one side surface of still another side fixing member 4. This arrangement saves the internal space of the fuselage, reduces the overall weight of the aircraft, and improves the contact area of the side fixing members 4 with the floor beam 100, the fuselage frame 400, and the first fixing member 1 and the second fixing member 2, thereby improving the load transfer efficiency.

[0047] Optionally, the fixing device further comprises a third fixing member 6, which is connected to one side of the first fixing member 1 and one side of the second fixing member 2 in the length direction of the aircraft, and the lower side of the third fixing member 6 is used to connect with the fuselage frame 400. By arranging the third fixing member 6, the loads borne by any one of the first fixing member 1 and the second fixing member 2 can be further dispersed and transferred to the fuselage frame 400, thereby improving the use reliability of the fixing device.

[0048] In order to save the internal space of the fuselage and reduce the overall weight of the aircraft, the third fixing member 6 is optionally in the form of a plate, and the thickness direction of the third fixing member 6 is parallel to the length direction of the aircraft.

[0049] Exemplarily, the lower side of the third fixing member 6 is shaped to match the fuselage frame 400, the first fixing member 1 and the second fixing member 2 are both perpendicularly connected to one side surface of the third fixing member 6, and the side fixing members 4 are connected between the upper side of the third fixing member 6 and the floor beam 100. This arrangement increases the connection area of the third fixing member 6 with the fuselage frame 400, the first fixing member 1, the second fixing member 2, and the side fixing members 4, thereby improving the load transfer efficiency and increasing the structural rationality.

[0050] It is worth mentioning that the third fixing member 6 can be arranged on both sides of the first fixing member 1 and the second fixing member 2 along the length direction of the fuselage, so as to further increase the structural strength and load transmission effect of the fixing device. The number of the third fixing member 6 can be arranged as required according to different fuselage structures, and is not limited here.

[0051] Optionally, the transition member 5 is in a strip shape, and the transition member 5 is connected to the first fixing member 1 and the second fixing member 2 at both ends of the length direction of the transition member 5. This arrangement can reduce the weight of the transition member 5 and the occupied space of the transition member 5 under the premise of balancing the load of the first fixing member 1 and the second fixing member 2, thereby improving the structural rationality of the fixing device.

[0052] Optionally, the cross section of the transition member 5 is in a U shape or an I shape. This arrangement can further reduce the weight of the transition member 5 and increase the structural strength of the transition member 5.

[0053] Exemplarily, the two actuator joints 500 each include a connecting portion and a mounting portion connected to each other, the connecting portion is movably connected to the actuator, the mounting portion of the actuator joint 500 is in a plate shape, the mounting portion of one actuator joint 500 is attached and mounted on one side of the first fixing member 1, and the mounting portion of the other actuator joint 500 is attached and mounted on one side of the second fixing member 2. This arrangement can increase the contact area between the mounting portion of the actuator joint 500 and the first fixing member 1 and the second fixing member 2, thereby increasing the connection strength and enhancing the load transmission effect.

[0054] Further, the mounting portion of the actuator joint 500 is provided with a plurality of mounting holes, the first fixing member 1 and the second fixing member 2 are provided with fastening holes, and the bolts pass through the mounting holes and the fastening holes to connect the mounting portion and the first fixing member 1 or the mounting portion and the second fixing member 2.

[0055] To strengthen the structural strength of the side fixing member 4, optionally, the side fixing member 4 is provided with a reinforcing rib on the side away from the actuator joint 500.

[0056] Optionally, the side fixing member 4 and the third fixing member 6 can be connected to the wing beam 600 on the side away from the actuator joint 500. This arrangement can further transmit the load to the wing beam 600, thereby improving the dispersion degree of the load and the use reliability of the fixing device.

[0057] Exemplarily, the third fixing member 6 and the wing beam 600 are integrally formed.

[0058] Optionally, the cross section of the fuselage frame 400 and the floor beam 100 is in a U shape. This arrangement can reduce the weight of the fuselage frame 400 and the floor beam 100, and at the same time, improve the structural strength of the fuselage frame 400 and the floor beam 100.

[0059] Optionally, the cross section of the longerons 200 is in the shape of Ω. This arrangement can reduce the weight of the longerons 200 and increase the structural strength, and the foot of the Ω-shaped longerons 200 is convenient for the bonding connection with the wall panels 300, thus improving the structural rationality of the fuselage.

[0060] Exemplarily, the first and second fixing members 1 and 2 are made of aluminum alloy material, and the top, side and third fixing members 3, 4 and 6 are made of aluminum alloy material or composite material.

[0061] The working process of the fixing device is as follows:

[0062] When the actuator is in action, the actuator joint 500 bears the load due to the reaction force of the actuator, and the actuator joint 500 transmits the load to the first and second fixing members 1 and 2, and the first and second fixing members 1 and 2 transmit part of the load to the floor beam 100 and the longerons 200 of the bottom of the aircraft, and the first and second fixing members 1 and 2 transmit part of the load to the wall panels 300 through the top fixing member 3, and then to the floor beam 100 again, and then the first and second fixing members 1 and 2 transmit the load to the floor beam 100 and the fuselage frame 400 through the side fixing member 4, and the first and second fixing members 1 and 2 transmit the load to each other through the transition member 5 to achieve balance, and then to the fuselage frame 400 through the third fixing member 6, so that the load borne by the actuator joint 500 is dispersed to the floor beam 100, the fuselage frame 400, the wall panels 300 and the longerons 200 inherent to the fuselage.

[0063] Note that the above are only the preferred embodiments of the present application and the technical principles applied. Those skilled in the art will understand that the present application is not limited to the specific embodiments described herein, and those skilled in the art can make various obvious changes, readjustments and substitutions without departing from the scope of the present application. Therefore, although the present application has been described in more detail through the above embodiments, the present application is not limited to the above embodiments, and can include more other equivalent embodiments without departing from the concept of the present application, and the scope of the present application is determined by the scope of the appended claims.

Claims

1. A fixing device for an actuator joint of a landing gear, characterized in that: The fixing device comprises a first fixing member (1) and a second fixing member (2) arranged opposite to each other, wherein the upper side of the first fixing member (1) is used to connect to a floor beam (100) of an aircraft, and the lower side is used to connect to a long stringer (200) at the bottom of the aircraft, the upper side of the second fixing member (2) is used to connect to the floor beam (100) of the aircraft, and the lower side is used to connect to another long stringer (200) at the bottom of the aircraft, and the side of the first fixing member (1) and the second fixing member (2) away from each other is used to install an actuator joint (500), and the fixing device further comprises a transition member (5), and the transition member (5) is connected between the first fixing member (1) and the second fixing member (2).

2. The fixing device according to claim 1, characterized in that The fixing device further comprises two top fixing members (3), wherein the top fixing members (3) can be connected between two adjacent floor beams (100), and one side of one top fixing member (3) is connected to the upper side of the first fixing member (1), and the other side is used to connect to the wall panel (300) of the aircraft, and the other side of the top fixing member (3) is connected to the upper side of the second fixing member (2), and the other side is used to connect to the wall panel (300) of the aircraft.

3. The fixing device according to claim 1, characterized in that The fixing device further comprises a side fixing member (4), wherein the side fixing member (4) can be connected between the floor beam (100) and the fuselage frame (400), the first fixing member (1) being connected to the side fixing member (4) on one side or both sides along the length direction of the aircraft, and the second fixing member (2) being connected to the side fixing member (4) on one side or both sides along the length direction of the aircraft.

4. The fixing device according to claim 1, characterized in that The fixing device further comprises a third fixing member (6), the third fixing member (6) being connected simultaneously to one side of the first fixing member (1) along the length direction of the aircraft and one side of the second fixing member (2) along the length direction of the aircraft, and the lower side of the third fixing member (6) is used for connecting to the fuselage frame (400).

5. The fixing device according to claim 4, characterized in that The third fixing member (6) is plate-shaped, and the thickness direction of the third fixing member (6) is parallel to the length direction of the aircraft.

6. The fixing device according to claim 1, characterized in that The first fixing member (1) and the second fixing member (2) are both plate-shaped, and the thickness directions of the first fixing member (1) and the second fixing member (2) are parallel to the width direction of the aircraft.

7. The fixing device according to claim 6, characterized in that Both the first fixing member (1) and the second fixing member (2) are provided with reinforcing ribs.

8. The fixing device according to any one of claims 1 to 7, characterized in that: The transition piece (5) is strip-shaped, and both ends of the transition piece (5) along its length direction are connected to the first fixing piece (1) and the second fixing piece (2) in a one-to-one correspondence.

9. The fixing device according to claim 8, characterized in that The cross section of the transition piece (5) is U-shaped or I-shaped.

10. An aircraft structure, characterized in that The aircraft structure comprises a fixing device according to any one of claims 1 to 9.

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