Hoisting device and hoisting method for lower thrust reverser of airplane

Abstract

The invention relates to the technical field of aircraft production and manufacturing, and particularly discloses an aircraft lower thrust reverser lifting device and method.The aircraft lower thrust reverser lifting device comprises a sling assembly, a self-balancing mechanism, a lifting frame, a turnover assembly, a clamp assembly and a control unit; the self-balancing mechanism is connected to the lower portion of the sling assembly, the hanging bracket is connected with the self-balancing mechanism, the overturning assembly is installed on the hanging bracket, the clamp assembly is connected to the tail end of the overturning assembly and used for clamping and fixing the lower reverse thrust cover, and the overturning assembly is in transmission connection with the clamp assembly and can drive the clamp assembly to rotate so as to drive the lower reverse thrust cover to overturn. The control unit can adjust the dynamic balance between the self-balancing mechanism and the horizontal plane. The integrated hoisting structure design is adopted, the lower thrust reverser can be hoisted once only through traveling equipment in the hoisting process, repeated disassembly and assembly are not needed, the hoisting process of the lower thrust reverser of the airplane is simplified, the assembly efficiency of the lower thrust reverser is improved, and the labor cost is saved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft production and manufacturing, and particularly relates to a device and method for hoisting a lower thrust reverser cover of an aircraft. BACKGROUND

[0002] The lower thrust reverser cover of an aircraft is composed of an upper thrust reverser cover and a lower thrust reverser cover, and is an external shell of a thrust reverser device, which is an important component of an engine nacelle. The main function of the lower thrust reverser cover is to cover and protect the thrust reverser mechanism, and to guide the airflow direction when the thrust reverser is activated to achieve the function of deceleration.

[0003] In the process of assembling an existing aircraft, the installation of the lower thrust reverser cover requires a lifting device, a lower thrust reverser cover clamp, and a turnover frame, which are three independent toolings. The engine lower thrust reverser cover needs to be lifted from the storage rack, and then turned over and installed on the hanger. Due to the structure and installation position of the lower thrust reverser cover, the above toolings need to be repeatedly disassembled and assembled multiple times in the entire installation process, and multiple operators are required to cooperate, which not only wastes time and effort, but also increases labor costs and greatly wastes assembly time.

[0004] Therefore, there is an urgent need for a device and method for hoisting a lower thrust reverser cover of an aircraft to solve the above problems. SUMMARY

[0005] The present application aims to provide a device and method for hoisting a lower thrust reverser cover of an aircraft, which can simplify the hoisting process of the lower thrust reverser cover of an aircraft, effectively improve the assembly efficiency, and save labor costs.

[0006] To achieve the above purpose, the present application adopts the following technical solutions:

[0007] On the one hand, the present application provides a device for hoisting a lower thrust reverser cover of an aircraft, comprising:

[0008] a lifting cable assembly connected to a travelling crane device;

[0009] a self-balancing mechanism connected below the lifting cable assembly;

[0010] a lifting frame connected to the self-balancing mechanism;

[0011] a turnover assembly installed on the lifting frame;

[0012] a clamp assembly connected to the end of the turnover assembly and used for clamping and fixing the lower thrust reverser cover, the turnover assembly being drivingly connected to the clamp assembly and being capable of driving the clamp assembly to rotate to turn over the lower thrust reverser cover;

[0013] a control unit capable of adjusting the dynamic balance of the self-balancing mechanism and the horizontal plane.

[0014] As a preferred technical scheme of the aircraft under-reverse thrust cover hoisting device, the sling assembly comprises a manual hoist, a lifting ring and a connecting piece, the lifting ring is used for connecting the travelling block device, the self-balancing mechanism comprises a guide rail, a sliding piece and a driving assembly, the guide rail is fixedly installed on the hanger, the driving assembly is drivingly connected to the sliding piece and can drive the sliding piece to slide along the guide rail, one end of the manual hoist is connected to the lifting ring, the other end of the manual hoist is connected to the sliding piece, and the connecting piece is connected between the hanger and the lifting ring.

[0015] As a preferred technical scheme of the aircraft under-reverse thrust cover hoisting device, the driving assembly comprises a driving piece, a lead screw and a nut, the driving piece is drivingly connected to the lead screw and can drive the lead screw to rotate, the lead screw is threadedly connected to the nut, the sliding piece comprises a sliding block and a lifting lug, the lifting lug is connected to the other end of the manual hoist, the sliding block is slidingly arranged on the guide rail, and the nut is fixedly connected between the lifting lug and the sliding block.

[0016] As a preferred technical scheme of the aircraft under-reverse thrust cover hoisting device, the driving piece is a servo motor.

[0017] As a preferred technical scheme of the aircraft under-reverse thrust cover hoisting device, the self-balancing mechanism further comprises a first bearing and a second bearing, the first bearing and the second bearing are respectively arranged at two ends of the lead screw, an inner ring of the first bearing is fixedly connected to the lead screw, an outer ring of the first bearing is fixedly connected to the guide rail, an inner ring of the second bearing is fixedly connected to the lead screw, and an outer ring of the second bearing is fixedly connected to the guide rail.

[0018] As a preferred technical scheme of the aircraft under-reverse thrust cover hoisting device, the self-balancing mechanism further comprises an inclination sensor, the inclination sensor is used for detecting a tilt angle of the self-balancing mechanism relative to a horizontal plane in real time, and the control unit is communicatively connected to the inclination sensor.

[0019] As a preferred technical scheme of the aircraft under-reverse thrust cover hoisting device, the connecting piece comprises a first lifting rope and a second lifting rope, the hanger protrudes a first fixed lug and a second fixed lug, the first lifting rope is connected between the lifting ring and the first fixed lug, and the second lifting rope is connected between the lifting ring and the second fixed lug.

[0020] As a preferred technical scheme of the aircraft under-thrust reverser hoisting device, the turnover assembly comprises a driving motor, a speed reducer and a rotating disc, the output end of the driving motor is connected to the input end of the speed reducer, the output end of the speed reducer is connected to the rotating disc, and the aircraft under-thrust reverser hoisting device further comprises a turnover frame connected between the clamp assembly and the rotating disc.

[0021] As a preferred technical scheme of the aircraft under-thrust reverser hoisting device, the aircraft under-thrust reverser hoisting device further comprises a first limit switch and a second limit switch, the first limit switch and the second limit switch are both installed on the hanger, and the first limit switch and the second limit switch are used to limit the turnover angle of the turnover frame.

[0022] In another aspect, the present application also provides a hoisting method, which is implemented by the aircraft under-thrust reverser hoisting device according to any of the above schemes, and the hoisting method comprises the following steps:

[0023] S100: connecting the sling assembly to the travelling device;

[0024] S200: rotating the clamp assembly and grabbing the under-thrust reverser by the turnover assembly;

[0025] S300: operating the travelling device to lift the under-thrust reverser to a suitable position;

[0026] S400: rotating the clamp assembly by the turnover assembly to turn the under-thrust reverser to an installation state;

[0027] S500: operating the travelling device to move the under-thrust reverser to an installation position.

[0028] The present application has the following beneficial effects:

[0029] The present application provides an aircraft under-thrust reverser hoisting device and a hoisting method, which comprises a sling assembly, a self-balancing mechanism, a hanger, a turnover assembly, a clamp assembly and a control unit. The sling assembly is connected to a travelling device, the self-balancing mechanism is connected below the sling assembly, the hanger is connected to the self-balancing mechanism, the turnover assembly is installed on the hanger, the clamp assembly is connected to the end of the turnover assembly and is used to clamp and fix the under-thrust reverser, the turnover assembly is drivingly connected to the clamp assembly and can drive the clamp assembly to rotate to turn the under-thrust reverser, and the control unit can adjust the dynamic balance between the self-balancing mechanism and the horizontal plane. In this way, an integrated hoisting structure design is adopted, only one hoisting of the travelling device is needed in the hoisting process of the under-thrust reverser, and multiple disassembly and assembly are not needed, which greatly simplifies the hoisting process of the aircraft under-thrust reverser, effectively improves the assembly efficiency and saves labor cost. BRIEF DESCRIPTION OF DRAWINGS

[0030] Figure 1 Structure diagram of the aircraft under-thrust reverser hoisting device provided by the present application Figure One ;

[0031] Figure 2 Structure diagram of the self-balancing mechanism provided by the present application

[0032] Figure 3 Structure diagram of the hanger provided by the present application

[0033] Figure 4 Partial structure diagram of the hanger provided by the present application

[0034] Figure 5 Structure diagram of the turnover assembly provided by the present application

[0035] Figure 6 Structure diagram of the clamp assembly provided by the present application

[0036] Figure 7 Structure diagram of the clamp assembly and the under-thrust reverser provided by the present application

[0037] Figure 8 Structure diagram of the aircraft under-thrust reverser hoisting device provided by the present application Figure Two ;

[0038] Figure 9 Structure diagram of the aircraft under-thrust reverser hoisting device provided by the present application Figure Three ;

[0039] Figure 10 Structure diagram of the aircraft under-thrust reverser hoisting device provided by the present application Figure Four ;

[0040] Figure 11 Structure diagram of the aircraft under-thrust reverser hoisting device provided by the present application Figure Five .

[0041] Wherein:

[0042] 100, sling assembly; 200, self-balancing mechanism; 300, hanger; 400, turnover assembly; 500, clamp assembly; 600, control unit

[0043] 1, under-thrust reverser; 2, guide rail; 3, driving piece; 4, lead screw; 5, nut; 6, sliding block; 7, lifting lug; 8, first bearing; 9, second bearing; 10, inclination sensor; 11, first fixed lug; 12, second fixed lug; 13, driving motor; 14, speed reducer; 15, turntable; 16, turnover frame; 17, first limit switch; 18, second limit switch DETAILED DESCRIPTION

[0044] Embodiments of the present application are described below in detail, examples of which are shown in the drawings, wherein the same or similar notations represent the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the drawings are exemplary, and are intended to explain the present application, and cannot be understood as a limitation of the present application.

[0045] In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation of the present application. In addition, the terms "first" and "second" are only for the purpose of description, and cannot be understood as indicating or implying relative importance. Among them, the terms "first position" and "second position" are two different positions.

[0046] Unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connecting", "fixing" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected; 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] Unless otherwise explicitly specified and limited, "on" or "under" of the first feature to the second feature can include that the first feature and the second feature are in direct contact, or the first feature and the second feature are not in direct contact but are in contact through another feature between them. Moreover, the first feature "on", "above" and "above" the second feature includes that the first feature is directly above and obliquely above the second feature, or only indicates that the first feature is higher than the second feature in horizontal height. The first feature "below", "below" and "below" the second feature includes that the first feature is directly below and obliquely below the second feature, or only indicates that the first feature is lower than the second feature in horizontal height.

[0048] The technical solutions of the present application are further illustrated below by specific embodiments in conjunction with the drawings.

[0049] As Figures 1 to 11As shown, the embodiment provides an aircraft lower thrust reverser cover hoisting device, which comprises a sling assembly 100, a self-balancing mechanism 200, a hanger 300, a turnover assembly 400, a clamp assembly 500 and a control unit 600. The sling assembly 100 is connected to the travelling crane equipment. The self-balancing mechanism 200 is connected below the sling assembly 100. The hanger 300 is connected with the self-balancing mechanism 200. The turnover assembly 400 is installed on the hanger 300. The clamp assembly 500 is connected to the end of the turnover assembly 400 and is used for clamping and fixing the lower thrust reverser cover 1. The turnover assembly 400 is drivingly connected to the clamp assembly 500 and can drive the clamp assembly 500 to rotate to drive the lower thrust reverser cover 1 to overturn. The control unit 600 is installed on the hanger 300, and the control unit 600 can adjust the dynamic balance of the self-balancing mechanism 200 and the horizontal plane. In this way, an integrated hoisting structure design is adopted, and only one hoisting of the travelling crane equipment is required in the hoisting process of the lower thrust reverser cover 1, and multiple disassembly and assembly are not required, which greatly simplifies the aircraft lower thrust reverser cover 1 hoisting process, effectively improves the assembly efficiency, and saves labor cost.

[0050] Optionally, the sling assembly 100 comprises a manual hoist, a lifting ring and a connecting piece. The lifting ring is used for connecting the travelling crane equipment. The self-balancing mechanism 200 comprises a guide rail 2, a sliding piece and a driving assembly. The guide rail 2 is fixedly installed on the hanger 300. The driving assembly is drivingly connected to the sliding piece and can drive the sliding piece to slide along the guide rail 2. One end of the manual hoist is connected to the lifting ring, and the other end of the manual hoist is connected to the sliding piece. The connecting piece is connected between the hanger 300 and the lifting ring. In this way, the introduction of the self-balancing mechanism 200 can realize dynamic balance in the overturning process, improve safety and reliability, and further, the connecting piece provides safety redundancy, can realize self-balancing compensation, reduces the fatigue loss of the manual hoist under pressure alone, and if the manual hoist or the sliding piece is accidentally broken, the connecting piece can be used as an emergency load bearing structure to prevent the load from falling instantly.

[0051] Further, the connecting piece comprises a first lifting rope and a second lifting rope. The hanger 300 protrudes a first fixed lug 11 and a second fixed lug 12. The first lifting rope is connected between the lifting ring and the first fixed lug 11. The second lifting rope is connected between the lifting ring and the second fixed lug 12. It should be noted that the length of the lifting lug 7 of the manual hoist on the lifting ring and the self-balancing mechanism 200 can be adjusted to control whether the hoisting is completely by the manual hoist or by the manual hoist, the first lifting rope and the second lifting rope together.

[0052] Specifically, the embodiment exemplarily provides the technical scheme as follows: the driving assembly comprises a driving member 3, a lead screw 4 and a nut 5, the driving member 3 is in transmission connection with the lead screw 4 and can drive the lead screw 4 to rotate, the lead screw 4 is in threaded connection with the nut 5, the sliding member comprises a sliding block 6 and an ear 7, the ear 7 is connected to the other end of the hand chain block, the sliding block 6 is slidingly arranged on the guide rail 2, and the nut 5 is fixedly connected between the ear 7 and the sliding block 6.

[0053] Further, in order to realize high-precision control and high-efficiency power output, the driving member 3 is a servo motor.

[0054] Optionally, in order to better support the rotation of the lead screw 4, reduce friction, and ensure the precision and efficiency of the operation, the self-balancing mechanism 200 further comprises a first bearing 8 and a second bearing 9, the first bearing 8 and the second bearing 9 are arranged at two ends of the lead screw 4 respectively, the inner ring of the first bearing 8 is fixedly connected to the lead screw 4, the outer ring of the first bearing 8 is fixedly connected to the guide rail 2, the inner ring of the second bearing 9 is fixedly connected to the lead screw 4, and the outer ring of the second bearing 9 is fixedly connected to the guide rail 2.

[0055] Optionally, in order to improve the automation degree of self-adaptive leveling, the self-balancing mechanism 200 further comprises an inclination sensor 10, the inclination sensor 10 is used for detecting the inclination angle of the self-balancing mechanism 200 relative to the horizontal plane in real time, and the control unit 600 is in communication connection with the inclination sensor 10. In this way, the angle of the self-balancing mechanism 200 relative to the horizontal plane can be detected by the inclination sensor 10 and fed back to the control unit 600 in real time, and the control unit 600 can control the rotation direction and rotation speed of the driving member 3 and adjust the sliding of the sliding member on the guide rail 2 according to the change of the obtained real-time angle, so as to realize the dynamic balance of the self-balancing mechanism 200 relative to the horizontal plane.

[0056] Optionally, the turnover assembly 400 comprises a driving motor 13, a speed reducer 14 and a rotating disc 15, the output end of the driving motor 13 is connected to the input end of the speed reducer 14, the output end of the speed reducer 14 is connected to the rotating disc 15 to drive the rotating disc 15 to rotate, and the aircraft under-thrust cover hoisting device further comprises a turnover frame 16, which is connected between the clamp assembly 500 and the rotating disc 15. In this way, the introduction of the speed reducer 14 can further increase the output torque, adapt to the high load demand, and realize overload buffering, so as to prolong the service life of the driving motor 13. At the same time, the turnover frame 16 is a rigid connection structure, which can uniformly transmit the rotating torque of the rotating disc 15 to the clamp assembly 500, avoid local stress concentration, and reduce the deformation risk of the rotating disc 15 or the clamp assembly 500. Further, the driving motor 13 is a servo motor, and the speed reducer 14 adopts an RV speed reducer.

[0057] In the embodiment, the clamp assembly 500 has four connection points, each of which is connected to the lower thrust reverser cover 1 by a bolt to achieve the grasping of the lower thrust reverser cover 1.

[0058] Optionally, the aircraft lower thrust reverser cover hoisting device further comprises a first limit switch 17 and a second limit switch 18, both of which are installed on the hanger 300, and are used to limit the turning position of the turnover frame 16 in the forward and reverse directions.

[0059] The embodiment also provides a hoisting method, which is implemented by the aircraft lower thrust reverser cover hoisting device in the above scheme, and comprises the following steps:

[0060] S100: connecting the sling assembly 100 to the travelling crane device.

[0061] S200: tightening the manual hoist to lift the entire aircraft lower thrust reverser cover hoisting device by the manual hoist alone. At this time, within the full movement range of the sliding member in the self-balancing mechanism 200, both the first sling and the second sling are in a slack state. After the manual hoist is tightened, the turnover frame 16 is turned to the state of grasping the lower thrust reverser cover 1, as shown in FIG. 6. Figure 8 It should be noted that the dynamic balance of the aircraft lower thrust reverser cover hoisting device in the turning process is ensured by the control unit 600 through the self-balancing mechanism 200. Figure 8 S300: operating the travelling crane device to lift the aircraft lower thrust reverser cover hoisting device in the state of FIG. 6 to the lower thrust reverser cover 1 storage rack, and connecting the clamp assembly 500 and the lower thrust reverser cover 1 by four bolts, as shown in FIG. 7. Figure 9

[0062] S300: operating the travelling crane device to lift the aircraft lower thrust reverser cover hoisting device in the state of FIG. 6 to the lower thrust reverser cover 1 storage rack, and connecting the clamp assembly 500 and the lower thrust reverser cover 1 by four bolts, as shown in FIG. 7.

[0063] S400: operating the aircraft lower thrust reverser cover hoisting device to rotate the turnover assembly 400 to drive the clamp assembly 500 to rotate, so that the lower thrust reverser cover 1 is turned to the installation state, as shown in FIG. 8. Figure 10 It should be noted that the dynamic balance of the aircraft lower thrust reverser cover hoisting device in the turning process is ensured by the control unit 600 through the self-balancing mechanism 200. At the same time, the manual hoist in the sling assembly 100 is operated to straighten the two first slings and the second sling under tension, as shown in FIG. 9. Figure 11

[0064] S500: operating the travelling crane device to move the lower thrust reverser cover 1 to the installation position.

[0065] S600: installing the lower thrust reverser cover 1. It should be noted that during the installation process, if the roll angle attitude of the lower thrust reverser cover 1 needs to be fine-tuned, it can be achieved by manually fine-tuning the manual hoist.

[0066] ​​S700: After the lower thrust reverser cover 1 is installed, the clamp assembly 500 is removed from the lower thrust reverser cover 1 and moved away. At this time, the aircraft lower thrust reverser cover hoisting device is in the state as shown in Figure 1

[0067] Obviously, the above embodiments of the present application are only examples for clearly illustrating the present application, and are not intended to limit the implementation modes of the present application. Based on the above description, other different forms of changes or variations can be made by those skilled in the art. Here, all the implementation modes are not required or can not be exhausted. Any modification, equivalent replacement and improvement, etc. made 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. An aircraft lower thrust reverse cover hoisting device, characterized in that: include: A sling assembly (100), wherein the sling assembly (100) is connected to the driving equipment; A self-balancing mechanism (200), the self-balancing mechanism (200) being connected below the sling assembly (100); a hanger (300), the hanger (300) being connected to the self-balancing mechanism (200); a turning assembly (400), the turning assembly (400) being mounted on the hanger (300); A clamp assembly (500), the clamp assembly (500) being connected to the end of the flip assembly (400) and being used to clamp and fix the lower reverse thrust cover (1); the flip assembly (400) being transmission-connected to the clamp assembly (500) and being capable of driving the clamp assembly (500) to rotate, thereby driving the lower reverse thrust cover (1) to flip; A control unit (600) is provided, wherein the control unit (600) is capable of adjusting the dynamic balance between the self-balancing mechanism (200) and a horizontal plane.

2. The aircraft lower thrust reverser cover hoisting device according to claim 1, characterized in that: The sling assembly (100) includes a manual hoist, a lifting ring and a connecting piece, the lifting ring is used to connect the traveling equipment, the self-balancing mechanism (200) includes a guide rail (2), a sliding piece and a driving assembly, the guide rail (2) is fixedly installed on the hanger (300), the driving assembly is connected to the sliding piece and can drive the sliding piece to slide along the guide rail (2), one end of the manual hoist is connected to the lifting ring, the other end of the manual hoist is connected to the sliding piece, and the connecting piece is connected between the hanger (300) and the lifting ring.

3. The aircraft lower thrust reverser cover hoisting device according to claim 2, characterized in that: The driving assembly includes a driving member (3), a lead screw (4) and a nut (5); the driving member (3) is transmission-connected to the lead screw (4) and can drive the lead screw (4) to rotate; the lead screw (4) and the nut (5) are threadedly connected; the sliding member includes a slider (6) and a lifting ear (7); the lifting ear (7) is connected to the other end of the manual hoist; the slider (6) is slidably arranged on the guide rail (2); and the nut (5) is fixedly connected between the lifting ear (7) and the slider (6).

4. The aircraft lower thrust reverser cover hoisting device according to claim 3, characterized in that: The driving member (3) is a servo motor.

5. The aircraft lower thrust reverser cover hoisting device according to claim 3, characterized in that: The self-balancing mechanism further comprises a first bearing (8) and a second bearing (9), wherein the first bearing (8) and the second bearing (9) are respectively arranged at two ends of the lead screw (4), the inner ring of the first bearing (8) is fixedly connected to the lead screw (4), the outer ring of the first bearing (8) is fixedly connected to the guide rail (2), the inner ring of the second bearing (9) is fixedly connected to the lead screw (4), and the outer ring of the second bearing (9) is fixedly connected to the guide rail (2).

6. The aircraft lower thrust reverser cover hoisting device according to claim 2, characterized in that: The self-balancing mechanism (200) further comprises an inclination sensor (10), wherein the inclination sensor (10) is used to detect the inclination angle of the self-balancing mechanism (200) relative to a horizontal plane in real time, and the control unit (600) is communicatively connected to the inclination sensor (10).

7. The aircraft lower thrust reverser cover hoisting device according to claim 2, characterized in that: The connecting member includes a first hanging rope and a second hanging rope, and a first fixing lug (11) and a second fixing lug (12) are protruding from the hanger (300). The first hanging rope is connected between the hanging ring and the first fixing lug (11), and the second hanging rope is connected between the hanging ring and the second fixing lug (12).

8. The aircraft lower thrust reverser cover hoisting device according to claim 1, characterized in that: The flip assembly (400) includes a drive motor (13), a reducer (14) and a turntable (15), wherein the output end of the drive motor (13) is connected to the input end of the reducer (14), and the output end of the reducer (14) is connected to the turntable (15). The aircraft lower thrust reverse cover hoisting device also includes a flip frame (16), and the flip frame (16) is connected between the clamp assembly (500) and the turntable (15).

9. The aircraft lower thrust reverser cover hoisting device according to claim 8, characterized in that: The aircraft lower thrust reverse cover hoisting device further includes a first limit switch (17) and a second limit switch (18), wherein the first limit switch (17) and the second limit switch (18) are both installed on the hanger (300), and the first limit switch (17) and the second limit switch (18) are used to limit the flip angle of the flip frame (16).

10. A hoisting method, characterized in that: The lifting method is implemented by the aircraft lower thrust reverser cover lifting device according to any one of claims 1 to 9, and includes: S100: Hooking the sling assembly (100) to the driving equipment; S200: the flip assembly (400) drives the clamp assembly (500) to rotate and grab the lower reverse thrust cover (1); S300: operating the driving equipment to raise the lower reverse thrust cover (1) to a suitable position; S400: the flip assembly (400) drives the clamp assembly (500) to rotate, so as to flip the lower reverse thrust cover (1) to an installed state; S500: operating the driving equipment to move the lower reverse thrust cover (1) to an installation position.

Images