A flipping device and flipping attitude adjustment method for strut sleeve type landing gear

Abstract

The present application discloses a flipping device and flipping attitude adjustment method for a strut sleeve landing gear, comprising a load tray, a servo electric cylinder, an electric cylinder rotating seat, a flipping mechanism, and a locking mechanism. The flipping mechanism is fixed at the center of the load tray, and the two tires of the landing gear cross over the flipping mechanism and are placed on the load tray. The servo electric cylinder is connected to one end of the flipping mechanism, and the locking mechanism is installed at the other end of the flipping mechanism. The servo electric cylinder drives the flipping mechanism from being inclined 45° to the ground to being perpendicular to the ground, and flips the landing gear to a vertical position at the same time. The present application can realize quantitative control during the assembly of the landing gear, simplify the landing gear installation process, and reduce the safety hazards caused by manual assembly.

Description

Technical Field

[0001] The present application relates to the field of aircraft landing gear docking assembly in the aviation manufacturing industry, and specifically to an assembly device for rapid flipping and precise docking between a strut sleeve type landing gear and an aircraft fuselage docking intersection. Background Art

[0002] As the most common type of aircraft landing gear, the strut-and-sleeve landing gear is widely installed on various large and medium-sized aircraft bodies and is an indispensable and important component for aircraft take-off and landing. Therefore, the installation of the landing gear has become an indispensable and important part of the aircraft assembly process. Since the overall height of the strut-and-sleeve landing gear in the upright state is relatively high, it is often necessary to lift the aircraft body as a whole to a certain height, then transport the landing gear upright to the bottom of the aircraft body installation position, and lift it as a whole to the installation height to meet the needs of landing gear docking and assembly.

[0003] At present, there is no special tooling or equipment for the flipping and docking of strut-sleeve landing gear. In order to meet the height requirements for installing the landing gear, the height of the entire aircraft needs to be lifted higher than the overall height of the landing gear after it is erected. The higher the aircraft body is lifted, the greater the risk. Therefore, the purpose of the patent of this invention is to simplify the landing gear installation process, reduce the safety hazards caused by manual assembly, and reduce a series of risks caused by the overall elevation of the aircraft body during the final assembly of the aircraft. Summary of the invention

[0004] The purpose of the present application is to provide a high-efficiency and high-precision flipping and docking device for aircraft strut-sleeve landing gear, to ensure that the strut-sleeve landing gear is assembled quickly, accurately and reliably, and to improve the quality of the landing gear docking assembly.

[0005] A flipping device for a strut sleeve type landing gear comprises a carrying tray, a servo electric cylinder, an electric cylinder rotating seat, a flipping mechanism, and a locking mechanism. The flipping mechanism is an L-shaped rotating arm structure. The flipping mechanism is fixed at the center position of the carrying tray. Two tires of the landing gear cross over the flipping mechanism and are placed on the carrying tray. The servo electric cylinder is fixed on the electric cylinder rotating seat. The electric cylinder rotating seat is fixed at the edge position of one side of the carrying tray. The servo electric cylinder is connected to one end of the flipping mechanism. The locking mechanism is installed at the other end of the flipping mechanism. The servo electric cylinder drives the flipping mechanism from being inclined 45° to the ground to being perpendicular to the ground, and flips the landing gear to a vertical position at the same time. The flip mechanism includes a rotating base, a pin shaft, a rotating arm, a supporting arm, and a rotating connecting shaft. The rotating base is fixed on the carrying tray. The rotating arm and the rotating base are movably connected through a pin shaft. One end of the rotating arm is connected to the ball joint bearing at the end of the servo electric cylinder through a pin shaft. The supporting arm is connected to the other end of the rotating arm through a rotating connecting shaft. The supporting arm can rotate around the rotating connecting shaft. The upper end of the supporting arm has a long slot hole connected to the locking mechanism, and the locking mechanism can slide in the long slot hole. The locking mechanism includes a nylon wheel, a locking knob, a connecting hook, a locking handle, and an ear connecting shaft. The ear connecting shaft passes through the nylon wheel, and the ear connecting shaft cooperates with the ear structure on the landing gear. Locking knobs are fixed at both ends of the ear connecting shaft, and connecting hooks are fixed on the outside of the locking knobs at both ends. The connecting hooks are connected as a whole by a locking handle passing through the long slot hole.

[0006] A method for turning over and adjusting the posture of a strut-sleeve landing gear comprises the following steps:

[0007] Step 1: Place the tires of the landing gear on the load tray;

[0008] Step 2: After the ear structure on the landing gear strut is connected to the locking mechanism of the flip device, it is fixed in the long slot hole of the support arm. At this time, the landing gear strut is in a tilted state at a certain angle;

[0009] Step 3: Use the servo electric cylinder to control the position of the flip mechanism. By quantitatively controlling the extension and retraction of the servo electric cylinder, the landing gear strut rotates around the center of the landing gear axle and can stop at any position to achieve the purpose of adjusting the overall attitude of the landing gear, that is, to meet the attitude adjustment of the A-direction degree of freedom.

[0010] Beneficial effects: The present invention provides a flipping and attitude adjustment device for a strut sleeve landing gear, which uses the extension and retraction of an electric servo cylinder to control the state adjustment of the landing gear strut. The servo control technology and the non-coaxial rotation technology are combined to accurately control the flipping of the landing gear strut. The quantitative control during the assembly of the landing gear can be achieved, the landing gear installation process can be simplified, the safety hazards caused by manual assembly can be reduced, the assembly accuracy of aircraft components can be greatly improved, and a series of risks caused by the overall elevation of the fuselage during the aircraft assembly process can be reduced.

[0011] The present application is described in further detail below in conjunction with the accompanying drawings of the embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 Schematic diagram of the components of the flip device

[0013] Figure 2 This is a schematic diagram of the flip mechanism structure

[0014] Figure 3 Schematic diagram of the locking mechanism

[0015] Figure 4 This is a schematic diagram of the overall layout of the flip device and landing gear

[0016] Figure 5 This is a schematic diagram of the flip device and landing gear after flipping

[0017] Explanation of numbers in the figure: 1 carrying tray; 2 servo electric cylinder; 3 electric cylinder rotating seat; 4 flip mechanism; 5 locking mechanism; 6 rotating base; 7 pin shaft; 8 rotating arm; 9 supporting arm; 10 rotating connecting shaft; 11 nylon wheel; 12 locking knob; 13 connecting hook; 14 locking handle; 15 ear connecting shaft. DETAILED DESCRIPTION

[0018] Referring to the accompanying drawings, the present application is a device for realizing the flipping of a strut-sleeve type landing gear.

[0019] from Figure 1 In the figure, a flipping device for a strut sleeve type landing gear comprises a carrying tray 1, a servo electric cylinder 2, an electric cylinder rotating seat 3, a flipping mechanism 4, and a locking mechanism 5. The flipping mechanism 4 is an L-shaped rotating arm structure, and the flipping mechanism 4 is fixed at the center position of the carrying tray 1. The two tires of the landing gear cross over the flipping mechanism 4 and are placed on the carrying tray 1. The servo electric cylinder 2 is fixed on the electric cylinder rotating seat 3, and the electric cylinder rotating seat 3 is fixed at the edge position of one side of the carrying tray 1. The servo electric cylinder 2 is connected to one end of the flipping mechanism 4, and the locking mechanism 5 is installed at the other end of the flipping mechanism 4. The servo electric cylinder 2 drives the flipping mechanism 4 from being inclined at 45° to the ground to being perpendicular to the ground, and at the same time flips the landing gear to a vertical position.

[0020] from Figure 2In the middle, the flipping mechanism 4 includes a rotating base 6, a pin 7, a rotating arm 8, a support arm 9, and a rotating connecting shaft 10. The flipping mechanism 4 is an L-shaped foldable rotating arm rigid body. The rotating base 6 is fixed on the carrying tray 1. The rotating arm 8 and the rotating base 6 are movably connected through an axle pin. One end of the rotating arm 8 is connected to the ball joint bearing at the end of the servo electric cylinder 2 through the pin 7. The support arm 9 is connected to the other end of the rotating arm 8 through the rotating connecting shaft 10. The support arm 9 can rotate around the rotating connecting shaft 10. The upper end of the support arm 9 has a long slot hole connected to the locking mechanism 5, and the locking mechanism 5 can slide in the long slot hole.

[0021] from Figure 3 As can be seen from the middle, the locking mechanism 5 includes a nylon wheel 11, a locking knob 12, a connecting hook 13, a locking handle 14, and an ear connecting shaft 15. The ear connecting shaft 15 is a round tube with threads at both ends. The ear connecting shaft 15 passes through the nylon wheel 11 and cooperates with the ear structure on the landing gear. Locking knobs 12 are fixed at both ends of the ear connecting shaft 15, and connecting hooks 13 are fixed on the outside of the locking knobs 12 at both ends. The connecting hooks 13 are connected as a whole by a locking handle 14 passing through the long slot.

[0022] from Figure 4 In the middle view, the telescopic end of the servo electric cylinder 2 is in the extended state, which can drive the flip mechanism 4 and the landing gear to rotate around the axis of the landing gear tire, and the landing gear forms a 45° inclination angle with the ground.

[0023] from Figure 5 In the middle view, the telescopic end of the servo electric cylinder 2 is in a retracted state, driving the flipping mechanism 4 and the landing gear to rotate around the axis of the landing gear tire. At this time, the landing gear flips together with the flipping mechanism to a state perpendicular to the ground.

[0024] A method for turning over and adjusting the posture of a strut-sleeve landing gear comprises the following steps:

[0025] Step 1: Place the tire of the landing gear on the carrying tray 1;

[0026] Step 2: After the ear structure on the landing gear strut is connected to the locking mechanism 5 of the flip device, it is fixed in the long slot hole of the support arm 9. At this time, the landing gear strut is in a tilted state at a certain angle;

[0027] Step 3: Use the servo electric cylinder 2 to control the position of the flip mechanism 4. By quantitatively controlling the extension and contraction of the servo electric cylinder 2, the landing gear strut rotates around the center of the landing gear axle and can stop at any position to achieve the purpose of adjusting the overall attitude of the landing gear, that is, to meet the attitude adjustment of the A-direction degree of freedom.

[0028] This patent considers the use of servo control technology and non-coaxial rotation technology to make up for the lack of height space at the lower end of the aircraft and realize the function of arbitrary rotation of the strut sleeve landing gear within a certain angle range. The strut of the landing gear rotates around the central axis of the tire, and the rotation center of the flipping mechanism that drives the strut is below the central axis position of the landing gear tire. Therefore, the length of the locking mechanism that locks the landing gear strut in the normal direction will change with a certain displacement as the angle changes. The device adopts servo control technology and non-coaxial rotation technology to meet the flexible adjustment of the landing gear flipping and the installation requirements of adjustable rotation angle.

Claims

1. A method for turning over and adjusting the attitude of a strut-sleeve landing gear, characterized in that A flipping device for a support sleeve type landing gear is used, the device comprises a carrying tray, a servo electric cylinder, an electric cylinder rotating seat, a flipping mechanism, and a locking mechanism. The flipping mechanism is an L-shaped rotating arm structure, the flipping mechanism is fixed at the center position of the carrying tray, the two tires of the landing gear cross over the flipping mechanism and are placed on the carrying tray, the servo electric cylinder is fixed on the electric cylinder rotating seat, the electric cylinder rotating seat is fixed at the edge position of one side of the carrying tray, the servo electric cylinder is connected to one end of the flipping mechanism, the locking mechanism is installed at the other end of the flipping mechanism, the telescopic end of the servo electric cylinder is in an extended state, driving the flipping mechanism and the landing gear to rotate around the axis of the landing gear tire, the landing gear forms a 45° inclination angle with the ground, the telescopic end of the servo electric cylinder is in a retracted state, driving the flipping mechanism and the landing gear to rotate around the axis of the landing gear tire, at this time the landing gear flips with the flipping mechanism to a state perpendicular to the ground, The flip mechanism comprises a rotating base, a pin shaft, a rotating arm, a supporting arm, and a rotating connecting shaft. The rotating base is fixed on the carrying tray. The rotating arm and the rotating base are movably connected through an axle pin. One end of the rotating arm is connected to the ball joint bearing of the end of the servo electric cylinder through the pin shaft. The supporting arm is connected to the other end of the rotating arm through a rotating connecting shaft. The supporting arm can rotate around the rotating connecting shaft. The upper end of the supporting arm is provided with a long slot hole connected to the locking mechanism. The locking mechanism can slide in the long slot hole. The locking mechanism comprises a nylon wheel, a locking knob, a connecting hook, a locking handle, and an ear connecting shaft. The ear connecting shaft passes through the nylon wheel. The ear connecting shaft cooperates with the ear structure on the landing gear. Locking knobs are fixed at both ends of the ear connecting shaft. Connecting hooks are fixed on the outer sides of the locking knobs at both ends. The connecting hooks are connected as a whole by a locking handle passing through the long slot hole. The flip posture adjustment method comprises the following steps: Step 1: Place the tires of the landing gear on the load tray; Step 2: After the ear structure on the landing gear strut is connected to the locking mechanism of the flip device, it is fixed in the long slot hole of the support arm. At this time, the landing gear strut is in a tilted state at a certain angle; Step 3: Use the electric servo cylinder to control the position of the flip mechanism. By quantitatively controlling the extension and retraction of the electric servo cylinder, the landing gear strut rotates around the center of the landing gear axle and can stop at any position to achieve the purpose of adjusting the overall attitude of the landing gear, that is, to meet the attitude adjustment of the A-direction degree of freedom.

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