Auxiliary mounting device for aircraft fuel tank covering cap

Abstract

The utility model provides an auxiliary installation device for an airplane fuel tank opening cover, and belongs to the technical field of airplane overhaul. The device is simple and flexible in structure, convenient to adjust, good in aircraft fuel tank opening cover grabbing effect and good in aircraft assembly assisting effect. Two hanging frames of the device are clamped on an aircraft wing, a cross beam is horizontally arranged, the two hanging frames are sleeved with the two ends of the cross beam respectively, a transverse groove is formed in the cross beam in the length direction, a groove opening of the transverse groove is communicated with the outside on the side vertical face, facing the aircraft wing, of the cross beam, and two linear motors with the same length are fixedly installed at the bottom of the transverse groove in a full laying mode. The two suction assemblies are fixedly installed on the sliding plates of the two linear motors correspondingly and cooperatively grab the aircraft fuel tank opening cover. The device is adjustable in structure, capable of being adjusted in the height direction and the width direction according to installation requirements, high in adaptability, high in flexibility and good in auxiliary effect, the device is installed on an aircraft wing in an adsorption mode and used for grabbing an aircraft fuel tank opening cover, hanging installation is stable, and damage to the skin of an aircraft is avoided.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft maintenance technology, and in particular relates to an auxiliary installation device for an aircraft fuel tank cap. Background Technology

[0002] During the installation of aircraft fuel tank caps, due to the large size of the aircraft, the fuel tank caps are also large. When technicians install the fuel tank caps on the aircraft wings, it is difficult to operate independently, and it is impossible to perform the action of holding and installing the caps with one hand. Therefore, it is necessary to have additional technicians to ensure that at least one person holds the cap and another person performs the installation and connection. This consumes human resources. Therefore, there is a need for a device that can assist technicians in installing aircraft fuel tank caps during the aircraft assembly process, helping them to complete the installation of aircraft fuel tank caps and reducing the difficulty of installation and connection. Utility Model Content

[0003] To address the problems existing in the background art, this utility model provides an auxiliary installation device for aircraft fuel tank caps. The device has a simple and flexible structure, is easy to adjust, has a good gripping effect on aircraft fuel tank caps, and provides good assistance in aircraft assembly.

[0004] The technical solution adopted by this utility model to solve its technical problem is: an auxiliary installation device for an aircraft fuel tank cap, including a crossbeam, two mounting brackets, two linear motors and two suction components. The two mounting brackets are clamped on the aircraft wing. The crossbeam is horizontally arranged, and the two ends of the crossbeam are respectively fitted onto the two mounting brackets. A transverse groove is opened on the crossbeam along its length. The opening of the transverse groove is open to the outside on the side of the crossbeam facing the aircraft wing. Two linear motors of equal length are fixedly installed at the bottom of the transverse groove. The two suction components are respectively fixedly installed on the sliding plates of the two linear motors. The two suction components work together to grip the aircraft fuel tank cap.

[0005] Each of the mounting brackets includes a connecting rod and two positioning plates. The two positioning plates are respectively hinged to both ends of the connecting rod. Multiple adsorption plates are fixedly installed on the end of each positioning plate away from the connecting rod. Each adsorption plate is located on the end face of each positioning plate facing the aircraft wing. Each adsorption plate has a vent hole along its axis. An air pump is fixedly installed on each positioning plate. The air pump nozzle is connected to the vent hole of the adsorption plate.

[0006] Each of the positioning plates is hinged to the connecting rod by a locking bolt. A nut is fixedly embedded on the end face of the positioning plate at the end through which the locking bolt protrudes. The locking bolt is inserted between the positioning plate and the connecting rod and screwed into the nut.

[0007] Each of the aforementioned suction components includes a sliding base, a hydraulic rod, and a flipping seat, i.e., a second suction plate. The sliding base is fixedly connected to the slide plate of the linear motor. The base end of the hydraulic rod is fixedly connected to the end face of the sliding base away from the linear motor. The telescopic end of the hydraulic rod is hinged to the flipping seat. The second suction plate is fixedly installed on the end face of the flipping seat facing the aircraft wing. A vent hole is opened in the middle of the second suction plate along the axis. An air pump is fixedly installed on the flipping seat. The air pump nozzle is connected to the vent hole of the second suction plate.

[0008] A stepper motor is fixedly embedded at the telescopic end of the hydraulic rod, and the flipping seat is fixedly connected to the drive end of the stepper motor.

[0009] The crossbeam has mounting slots at both ends of its face away from the suction assembly. The mounting slots extend longitudinally through the upper and lower ends of the crossbeam. The cross-sectional shape of the mounting slots matches the cross-sectional shape of the connecting rod. The connecting rod is inserted into the mounting slot. A clamping cover plate is installed on the slot opening. The clamping cover plate is detachably fixed to the crossbeam by mounting bolts. An adjusting gear is rotatably installed on the bottom of the mounting slot. The connecting rod has fully machined teeth on its end face facing the bottom of the mounting slot. The adjusting gear meshes with the gearbox. A drive motor is fixedly installed in the crossbeam. The drive shaft of the drive motor is driven by the adjusting gear.

[0010] The beneficial effects of this utility model are as follows: The mounting bracket of the device is a connecting structure, which can be adapted to the wings of various aircraft models for angle adjustment, and has strong adaptability; the crossbeam of the device can be adjusted in position, and two linear motors are installed in the crossbeam, which enables the device to adapt to the aircraft fuel tank cap to be installed in both height and width directions, which is highly flexible and has a good auxiliary effect; the device is installed on the aircraft wing by adsorption in combination with an adsorption plate and an air pump, and holds the aircraft fuel tank cap by adsorption, which is stable and does not damage the aircraft skin. Attached Figure Description

[0011] In the attached diagram:

[0012] Figure 1 This is a schematic diagram of the overall structure of the utility model;

[0013] Figure 2 This is a schematic diagram of the overall structural layout of the utility model;

[0014] Figure 3 yes Figure 2 Enlarged view of part A in the middle;

[0015] Figure 4 This is a schematic diagram of the utility model mounting bracket structure;

[0016] Figure 5 This is a schematic diagram of the disassembly of the utility model beam installation structure;

[0017] In the diagram: 1. Hanging rack; 2. Crossbeam; 3. Linear motor; 4. Holding assembly; 11. Positioning plate; 12. Connecting rod; 13. Adsorption plate one; 14. Locking bolt; 21. Insertion slot; 22. Adjustment gear; 23. Clamping cover plate; 24. Mounting bolt; 41. Sliding base; 42. Hydraulic rod; 43. Tilting seat; 44. Adsorption plate two. Detailed Implementation

[0018] The present invention will now be described in further detail with reference to the accompanying drawings. The drawings are simplified schematic diagrams, illustrating only the basic structure of the present invention, and therefore only show the components relevant to the present invention.

[0019] An auxiliary installation device for an aircraft fuel tank cap includes a crossbeam 2, two mounting brackets 1, two linear motors 3, and two suction components 4. The two mounting brackets 1 are clamped onto the aircraft wing. The crossbeam 2 is horizontally arranged, with its two ends respectively fitted onto the two mounting brackets 1. A transverse groove is formed along the length of the crossbeam 2, and the opening of the groove is open to the outside on the side of the crossbeam 2 facing the aircraft wing. Two linear motors 3 of equal length are fixedly installed at the bottom of the groove. The two suction components 4 are respectively fixedly installed on the sliding plates of the two linear motors 3. The two suction components 4 work together to grip the aircraft fuel tank cap, so as to assist technicians in installing the aircraft fuel tank cap at the refueling port of the aircraft wing.

[0020] Each mounting bracket 1 includes a connecting rod 12 and two positioning plates 11. The two positioning plates 11 are respectively hinged to both ends of the connecting rod 12. Multiple adsorption plates 13 are fixedly installed on the end of each positioning plate 11 away from the connecting rod 12. The adsorption plates 13 are all located on the end face of each positioning plate 11 facing the aircraft wing. Each adsorption plate 13 has a vent hole along the axis. An air pump is fixedly installed on each positioning plate 11. The air pump nozzle is connected to the vent hole of the adsorption plate 13. When the adsorption plate 13 is attached to the surface of the aircraft wing, the air pump operates to extract air, so that the adsorption plate 13 is tightly attached to the aircraft wing, thereby making the mounting bracket 1 stably clamped on the aircraft wing.

[0021] Each positioning plate 11 is hinged to the connecting rod 12 by a locking bolt 14. A nut is fixedly embedded on the end face of the locking bolt 14 on the positioning plate 11. The locking bolt 14 is inserted between the positioning plate 11 and the connecting rod 12 and screwed into the nut. The locking bolt 14 and the nut cooperate and are tightened, that is, clamping the positioning plate 11 and the connecting rod 12 and locking the included angle between the positioning plate 11 and the connecting rod 12. The locking bolt 14 and the nut are loosened, that is, a gap is created between the positioning plate 11 and the connecting rod 12, so that the included angle between the positioning plate 11 and the connecting rod 12 can be adjusted as needed. After the adjustment is completed, the locking bolt 14 is tightened.

[0022] Each of the aforementioned suction components 4 includes a sliding base 41, a hydraulic rod 42, and a flipping seat 43, i.e., a second suction plate 44. The sliding base 41 is fixedly connected to the slide plate of the linear motor 3. The base end of the hydraulic rod 42 is fixedly connected to the end face of the sliding base 41 away from the linear motor 3. The telescopic end of the hydraulic rod 42 is hinged to the flipping seat 43. The second suction plate 44 is fixedly installed on the end face of the flipping seat 43 facing the aircraft wing. A vent hole is opened in the middle of the second suction plate 44 along the axis. A second air pump is fixedly installed on the flipping seat 43. The air pump nozzle of the second air pump is connected to the vent hole of the second suction plate 44. When the second suction plate 44 is attached to the aircraft fuel tank cap, the second air pump operates to extract air, thereby making the second suction plate 44 tightly adhere to the outer wall of the aircraft fuel tank cap, thus allowing the suction component 4 to stably grip the aircraft fuel tank cap.

[0023] A stepper motor is fixedly embedded at the telescopic end of the hydraulic rod 42, and the flipping seat 43 is fixedly connected to the drive end of the stepper motor. The operation of the stepper motor drives the flipping seat 43 to flip and adjust its position at the end of the hydraulic rod 42.

[0024] The crossbeam 2 has two end faces facing away from the suction assembly 4 with embedded grooves 21. The embedded grooves 21 extend longitudinally through the upper and lower end faces of the crossbeam 2. The cross-sectional shape of the embedded grooves 21 matches the cross-sectional shape of the connecting rod 12. The connecting rod 12 is inserted into the embedded grooves 21. A clamping cover plate 23 is installed on the groove opening of the embedded groove 21. The clamping cover plate 23 is detachably fixed on the crossbeam 2 by mounting bolts 24. An adjusting gear 22 is rotatably installed on the bottom of the groove of the embedded groove 21. The end faces of the connecting rod 12 and the bottom of the groove of the embedded groove 21 are fully covered with machined teeth. The adjusting gear 22 meshes with the tooth box. A drive motor is fixedly embedded in the crossbeam 2. The drive shaft of the drive motor is driven to drive the adjusting gear 22. When the drive motor runs, it drives the adjusting gear 22 to rotate. The adjusting gear 22 meshes with the teeth. Because the connecting rod 12 is stationary, the crossbeam 2 is adjusted longitudinally along the connecting rod 12.

[0025] Working principle: Two positioning plates 11 are respectively hinged to the two ends of the connecting rod 12 by locking bolts 14 to form a hanging frame 1. After the two hanging frames 1 are assembled, two linear motors 3 are pre-installed in the horizontal groove of the crossbeam 2. The suction component 4 is fixedly installed on the slide plate of the linear motor 3. The crossbeam 2 is mounted between the two hanging frames 1. Two insert slots 21 are snapped onto the connecting rod 12. The adjusting gear 22 meshes with the teeth on the connecting rod 12. The clamping cover plate 23 is detachably fixed on the crossbeam 2 by mounting bolts 24. The assembly of the device is thus completed.

[0026] The device is clamped onto the aircraft wing, with two mounting brackets 1 positioned on either side of the location where the aircraft fuel tank cap will be installed. During clamping, the suction plates 13 on the two positioning plates 11 of each mounting bracket 1 are aligned with the surface of the aircraft wing. The air pump 1 is activated to extract air until the suction plates 13 are tightly adhered to the aircraft wing. Then, the height of the crossbeam 2 on the mounting bracket 1 is adjusted. During adjustment, the drive motor is activated to rotate the adjusting gear 22, which meshes with the teeth on the connecting rod 12 to adjust the position of the crossbeam 2 on the mounting bracket 1. The suction assembly 4 is adjusted to grip the aircraft fuel tank cap, and the aircraft fuel tank cap is placed on the suction plate 44. The air pump 2 is activated to extract air until the suction plate 44 is tightly adhered to the aircraft fuel tank cap.

[0027] When installing the aircraft fuel tank cap onto the aircraft wing, the stepper motor is adjusted to operate appropriately, causing the tilting seat 43 to rotate appropriately, so that the aircraft fuel tank cap rotates to the appropriate angle. The hydraulic rod 42 is adjusted to extend appropriately, so that the aircraft fuel tank cap and the aircraft wing are properly aligned. Then the operator performs the specific connection and installation procedures, such as riveting and bolt tightening, until the installation of the aircraft fuel tank cap is completed.

[0028] After installation, adjust the second air pump to run in reverse so that the second adsorption plate 44 detaches from the aircraft fuel tank cap. Then, start multiple first air pumps to run in reverse so that multiple adsorption plates 13 detach from the aircraft wing, and the entire device can be removed from the aircraft wing.

[0029] When installing aircraft fuel tank caps of different sizes, the two linear motors 3 are operated to adjust the position of the sliding base 41 and adjust the distance between the two suction components 4 to ensure that the two suction components 4 can work together to stably grip the aircraft fuel tank cap.

[0030] The above description is merely a preferred embodiment of this utility model and is not intended to limit the utility model. Various modifications and variations can be made to this utility model by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. An auxiliary installation device for an aircraft fuel tank cap, characterized in that: The device includes a crossbeam (2), two mounting brackets (1), two linear motors (3), and two suction components (4). The two mounting brackets (1) are clamped on the aircraft wing. The crossbeam (2) is horizontally arranged, with its two ends respectively fitted onto the two mounting brackets (1). A horizontal groove is opened along the length of the crossbeam (2), and the opening of the groove is connected to the outside on the side of the crossbeam (2) facing the aircraft wing. Two linear motors (3) of equal length are fixedly installed at the bottom of the groove. The two suction components (4) are respectively fixedly installed on the sliding plates of the two linear motors (3). The two suction components (4) work together to grip the aircraft fuel tank cap.

2. The auxiliary installation device for an aircraft fuel tank cap according to claim 1, characterized in that: Each of the mounting brackets (1) includes a connecting rod (12) and two positioning plates (11). The two positioning plates (11) are respectively hinged to both ends of the connecting rod (12). Multiple adsorption plates (13) are fixedly installed on the end of each positioning plate (11) away from the connecting rod (12). The adsorption plates (13) are all located on the end face of each positioning plate (11) facing the aircraft wing. Each adsorption plate (13) has a ventilation hole along the axis. Each positioning plate (11) has an air pump fixedly installed. The air pump nozzle is connected to the ventilation hole of the adsorption plate (13).

3. The auxiliary installation device for an aircraft fuel tank cap according to claim 2, characterized in that: Each of the positioning plates (11) is hinged to the connecting rod (12) by a locking bolt (14). A nut is fixedly embedded on the end face of the locking bolt (14) on the positioning plate (11). The locking bolt (14) is inserted between the positioning plate (11) and the connecting rod (12) and screwed into the nut.

4. An auxiliary installation device for an aircraft fuel tank cap according to claim 1 or 2, characterized in that: Each of the aforementioned suction components (4) includes a sliding base (41), a hydraulic rod (42), and a flipping seat (43), namely, a second suction plate (44). The sliding base (41) is fixedly connected to the slide plate of the linear motor (3). The base end of the hydraulic rod (42) is fixedly connected to the end face of the sliding base (41) away from the linear motor (3). The telescopic end of the hydraulic rod (42) is hinged to the flipping seat (43). The second suction plate (44) is fixedly installed on the end face of the flipping seat (43) facing the aircraft wing. A vent hole is opened in the middle of the second suction plate (44) along the axis. An air pump is fixedly installed on the flipping seat (43). The air pump nozzle is connected to the vent hole of the second suction plate (44).

5. The auxiliary installation device for an aircraft fuel tank cap according to claim 4, characterized in that: The telescopic end of the hydraulic rod (42) is fixedly fitted with a stepper motor, and the flipping seat (43) is fixedly connected to the drive end of the stepper motor.

6. The auxiliary installation device for an aircraft fuel tank cap according to claim 4, characterized in that: The crossbeam (2) has two end faces facing away from the suction assembly (4) with mounting grooves (21). The mounting grooves (21) extend longitudinally through the upper and lower end faces of the crossbeam (2). The cross-sectional shape of the mounting grooves (21) matches the cross-sectional shape of the connecting rod (12). The connecting rod (12) is inserted into the mounting grooves (21). A clamping cover plate (23) is installed on the groove opening of the mounting grooves (21). The clamping cover plate (23) is detachably and fixedly installed on the crossbeam (2) by mounting bolts (24). An adjusting gear (22) is rotatably installed on the bottom of the mounting grooves (21). The connecting rod (12) is fully covered with machined teeth on the end face facing the bottom of the mounting grooves (21). The adjusting gear (22) meshes with the gear box. A drive motor is fixedly installed in the crossbeam (2). The drive shaft of the drive motor is driven and connected to the adjusting gear (22).

Images