Passenger aircraft component loading mechanism and passenger aircraft assembly apparatus

Abstract

The present disclosure provides a passenger aircraft component feeding mechanism and a passenger aircraft assembly device; the passenger aircraft component feeding mechanism comprises a rack, a clamping assembly, a stroke limiting assembly and a follow-up limiting piece; the clamping assembly is arranged on the rack in a lifting manner; the stroke limiting assembly comprises a stroke limiting rod and two limiting components, the stroke limiting rod is installed on the rack; the stroke limiting rod is parallel to the lifting path of the clamping assembly, a reference position and at least two adjustment positions are sequentially arranged on the stroke limiting rod in the length direction, one limiting component is installed on the reference position, the other limiting component is detachably installed on any adjustment position, and a lifting movement space is formed between the two adjustment positions; when the follow-up limiting piece moves synchronously with the clamping assembly and lifts in the lifting movement space, the lifting height of the follow-up limiting piece is limited by the abutting of part of the follow-up limiting piece against the limiting component, so that the lifting height of the clamping assembly can be limited within the height range of the lifting movement space.

Description

Technical Field

[0001] This disclosure relates to the technical field of civil aircraft assembly, and in particular to a passenger aircraft component loading mechanism and passenger aircraft assembly equipment. Background Technology

[0002] Passenger aircraft are typically large, and their components are often characterized by their large size, heavy weight, and complex shape. To facilitate the loading and assembly of these components, most manufacturers use pneumatic clamping devices for aircraft parts, such as those disclosed in Chinese patent document CN115990907A, for automated loading. However, due to the varying heights of different aircraft components, the required lifting height of the clamping device often differs. Therefore, to ensure accurate loading of aircraft components by the clamping device, flexible control of the clamping device's feeding height is crucial. Utility Model Content

[0003] The purpose of this disclosure is to overcome the shortcomings of the prior art and provide a passenger aircraft component loading mechanism and passenger aircraft assembly equipment with more flexible control over the feeding height of the clamping device.

[0004] The purpose of this disclosure is achieved through the following technical solution:

[0005] A passenger aircraft component loading mechanism, comprising:

[0006] frame;

[0007] A clamping assembly, which is elliptical and mounted on the frame, is used to clamp aircraft parts;

[0008] The aircraft component loading mechanism also includes a travel limiting component and a follow-up limiting component;

[0009] The travel limiting component includes a travel measuring rod and two limiting components. The travel measuring rod is mounted on the frame. The travel measuring rod is parallel to the lifting path of the clamping component. A reference position and at least two adjustment positions are sequentially arranged along the length direction on the travel measuring rod. One of the limiting components is mounted on the reference position, and the other limiting component is detachably mounted on any of the adjustment positions. A lifting space is formed between the two adjustment positions. A follower limiting member is connected to the clamping component, and a portion of the follower limiting member is located within the lifting space. The follower limiting member is used to lift and lower with the clamping component, and a portion of the follower limiting member abuts against the limiting components to determine the lifting height of the clamping component within the height range of the lifting space.

[0010] In some embodiments, the travel measuring rod is provided with a mounting structure at each of the adjustment positions.

[0011] In some embodiments, the mounting structure is a mounting hole, in which a threaded connector is installed, and the threaded connector is threadedly connected to the corresponding limiting component.

[0012] In some embodiments, the mounting structures are evenly spaced apart.

[0013] In some embodiments, the frame is further provided with a clamping rod assembly, which includes a mounting base and a cover plate stacked on top of each other. The mounting base is fixedly connected to the frame, and a portion of the stroke measuring rod is disposed between the mounting base and the cover plate. The cover plate is locked to the mounting base to clamp and fix a portion of the stroke measuring rod to the clamping rod assembly.

[0014] In some embodiments, the stroke measuring rod has a guide waist-shaped groove, and the cover plate has a mating boss protruding into the guide waist-shaped groove.

[0015] In some embodiments, the aircraft component loading mechanism further includes a lifting assembly mounted on the frame, and a clamping assembly mounted on the telescopic end of the lifting assembly.

[0016] In some embodiments, the lifting assembly includes a fixed base, a lifting drive, a guide rod, and a carrying platform; the fixed base is fixedly connected to the frame, the lifting drive is mounted on the fixed base, and the clamping assembly is mounted on the telescopic rod of the lifting drive; the guide rod slides through the fixed base, the first end of the guide rod is connected to the clamping assembly, the second end of the guide rod is provided with the carrying platform, and the follow-up limiting member is fixedly mounted on the carrying platform.

[0017] In some embodiments, a retaining roller is rotatably provided on the limiting member, and a buffer slope is formed on the follower limiting member; the retaining roller abuts against the buffer slope to determine the lifting height of the clamping assembly within the height range of the lifting space.

[0018] A passenger aircraft assembly equipment includes a passenger aircraft component loading mechanism according to any of the above embodiments.

[0019] Compared with the prior art, this disclosure has at least the following advantages:

[0020] The aforementioned aircraft component loading mechanism, with its stroke measuring rod mounted on the frame parallel to the lifting path of the clamping assembly, and a reference position and at least two adjustment positions sequentially arranged along its length, forms a lifting space between a limiting component mounted on the reference position and a limiting component detachably mounted on any of the adjustment positions. When the follower limiting component moves synchronously with the clamping assembly and rises and falls within this lifting space, the follower limiting component reacts to the lifting height of the clamping assembly. By partially abutting against the limiting component, the lifting height of the follower limiting component is limited, thus restricting the lifting height of the clamping assembly within the height range of the lifting space. In this way, operators can adjust another limiting component to the corresponding adjustment position according to the installation height of different components, ultimately flexibly adjusting the height range of the lifting space and controlling the lifting height of the clamping assembly. Attached Figure Description

[0021] To more clearly illustrate the technical solutions of the embodiments of this disclosure, the accompanying drawings used in the embodiments will be briefly described below. It should be understood that the following drawings only show some embodiments of this disclosure and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram of the structure of a passenger aircraft component loading mechanism according to an embodiment of the present disclosure;

[0023] Figure 2 for Figure 1 The exploded view of the passenger aircraft component loading mechanism shown is shown.

[0024] Figure 3 for Figure 1 A magnified view of the area shown at point A in the middle.

[0025] Figure label:

[0026] 100. Rack;

[0027] 200. Clamping assembly;

[0028] 300. Stroke limiting component; 310. Limiting component; 3110. Supporting roller; 320. Stroke measuring rod; 3210. Reference position; 3220. Adjustment position; 3201. Mounting hole; 311. Upper limiting component; 312. Lower limiting component; 3202. Lifting space; 3203. Guide slot;

[0029] 400, Follow-up limiting component 400; 401, Buffer bevel;

[0030] 500. Clamping rod assembly; 510. Mounting base; 520. Cover plate;

[0031] 600, Lifting assembly; 610, Mounting base; 6101, Sliding hole; 620, Lifting drive; 630, Guide rod; 640, Load-bearing platform. Detailed Implementation

[0032] To facilitate understanding of this disclosure, a more complete description will be given below with reference to the accompanying drawings, which illustrate preferred embodiments of the present disclosure. However, this disclosure can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided to provide a more thorough and complete understanding of the disclosure.

[0033] It should be noted that when an element is referred to as being "fixed to" another element, it can be directly attached to the other element or there may be an intervening element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementation.

[0034] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this disclosure belongs. The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of this disclosure. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0035] To better understand the technical solutions and beneficial effects of this disclosure, the following detailed description is provided in conjunction with specific embodiments:

[0036] Please see Figure 1An embodiment of the passenger aircraft component loading mechanism includes a frame 100, a clamping assembly 200, a travel limiting assembly 300, and a follower limiting member 400. The clamping assembly 200 is ellipsably mounted on the frame 100 and is used to clamp aircraft components. The travel limiting assembly 300 includes a travel measuring rod 320 and two limiting members 310. The travel measuring rod 320 is mounted on the frame 100. The travel measuring rod 320 is parallel to the lifting path of the clamping assembly 200, and a reference position 3210 and at least two adjustment positions 3220 are sequentially provided along the length direction on the travel measuring rod 320. One limiting component 310 is installed at the reference position 3210, and the other limiting component 310 is detachably installed at any adjustment position 3220, forming a lifting space 3202 between the two adjustment positions 3220. A follower limiting component 400 is connected to the clamping assembly 200, and a portion of the follower limiting component 400 is located within the lifting space 3202. The follower limiting component 400 is used to move up and down with the clamping assembly 200, and a portion of the follower limiting component 400 abuts against the limiting component 310 to determine the lifting height of the clamping assembly 200 within the height range of the lifting space 3202. The clamping assembly 200 can be a gripper or a claw.

[0037] It is understood that since the stroke measuring rod 320 installed on the frame 100 is parallel to the lifting path of the clamping assembly 200, and the stroke measuring rod 320 is provided with a reference position 3210 and at least two adjustment positions 3220 in sequence along the length direction, and a lifting space 3202 is formed between the limiting member 310 installed on the reference position 3210 and the limiting member 310 that can be detachably installed on any one of the adjustment positions 3220, when the follower limiting member 400 moves synchronously with the clamping assembly 200 and rises and falls within the lifting space 3202, the follower limiting member 400 can respond to the lifting height of the clamping assembly 200, thereby limiting the lifting height of the follower limiting member 400 by partially abutting against the limiting member 310, thereby limiting the lifting height of the clamping assembly 200 within the height range of the lifting space 3202. In this way, the staff can adjust another limiting component 310 to the corresponding adjustment position 3220 according to the installation height of different components, and finally flexibly adjust the height range of the lifting and lowering space 3202 and control the lifting and lowering height of the clamping component 200.

[0038] Please see Figure 2In this embodiment, the two limiting components 310 are an upper limiting component 311 and a lower limiting component 312. The lower limiting component 312 is installed at the reference position 3210, and the upper limiting component 311 is detachably installed at any adjustment position 3220. A lifting space 3202 is formed between the upper limiting component 311 and the lower limiting component 312. Part of the follower limiting member 400 abuts against the upper limiting component 311 or the lower limiting component 312 to determine the lifting height of the clamping assembly 200 within the height range of the lifting space 3202.

[0039] Please see Figure 1 and Figure 2 In some embodiments, the travel measuring rod 320 has mounting structures at each adjustment position 3220. It is understood that by providing mounting structures at each adjustment position 3220 on the travel measuring rod 320, when another limiting member 310 is at the corresponding adjustment position 3220, the mounting structure at the corresponding adjustment position 3220 can form a detachable connection with the other limiting member 310. In this embodiment, the mounting structure at the corresponding adjustment position 3220 can form a detachable connection with the lower limiting member 312.

[0040] In some embodiments, the mounting structure is a mounting hole 3201, within which a threaded connector (not shown) is installed. The threaded connector is threadedly connected to the corresponding limiting member 310. It is understood that by threading the connector in the mounting hole 3201 to the corresponding limiting member 310, the limiting member 310 can be flexibly attached and detached from the threaded connector. This facilitates flexible adjustment of the limiting member 310 to different adjustment positions 3220, thereby flexibly adjusting the height range of the lifting space 3202 and controlling the lifting height of the clamping assembly 200. Please refer to... Figure 2 In this embodiment, the threaded connector is threadedly connected to the corresponding upper limiting member 311. The threaded connector is a screw or bolt.

[0041] Please see Figure 1 and Figure 3 In some embodiments, the mounting structures are evenly spaced apart. It is understood that because the mounting structures are evenly spaced apart, when the upper limiting component 311 is mounted on different mounting structures, the position of the upper limiting component 311 can change evenly, thereby uniformly adjusting the height change of the lifting space 3202.

[0042] Please see Figure 2In some embodiments, the frame 100 is further provided with a clamping rod assembly 500, which includes a mounting base 510 and a cover plate 520 stacked together. The mounting base 510 is fixedly connected to the frame 100, and a portion of the stroke measuring rod 320 is disposed between the mounting base 510 and the cover plate 520. The cover plate 520 is locked to the mounting base 510 to clamp and fix a portion of the stroke measuring rod 320 to the clamping rod assembly 500. It can be understood that since a portion of the stroke measuring rod 320 is disposed between the mounting base 510 and the cover plate 520, when the cover plate 520 and the mounting base 510 are locked together, the position of the stroke measuring rod 320 can be clamped and fixed by the cover plate 520 and the mounting base 510 together.

[0043] Please see Figure 1 and Figure 2 In some embodiments, the travel measuring rod 320 has a guide waist-shaped groove 3203, and the cover plate 520 has a mating boss (not shown) protruding into the guide waist-shaped groove 3203. It can be understood that because the cover plate 520 has a mating boss protruding into the guide waist-shaped groove 3203 of the travel measuring rod 320, when it is necessary to adjust the travel measuring rod 320 to rise or fall, the connection strength between the cover plate 520 and the mounting base 510 can be reduced, allowing the travel measuring rod 320 to rise or fall between the cover plate 520 and the mounting base 510. At this time, the mating boss can slide and interfere with the groove wall of the guide waist-shaped groove 3203, allowing the travel measuring rod 320 to rise or fall along the length direction of the guide waist-shaped groove 3203. Then, the mounting base 510 and the cover plate 520 are locked together.

[0044] Please see Figure 1 In some embodiments, the aircraft component loading mechanism further includes a lifting assembly 600 mounted on the frame 100, and a clamping assembly 200 mounted on the telescopic end of the lifting assembly 600. It is understood that by mounting the clamping assembly 200 on the telescopic end of the lifting assembly 600, and the lifting assembly 600 being mounted on the frame 100, the clamping assembly 200 can be driven to rise or fall relative to the frame 100 via the lifting assembly 600.

[0045] Please see Figure 1In some embodiments, the lifting assembly 600 includes a fixed base 610, a lifting driver 620, a guide rod 630, and a support platform 640; the fixed base 610 is fixedly connected to the frame 100, the lifting driver 620 is mounted on the fixed base 610, and the clamping assembly 200 is mounted on the telescopic rod of the lifting driver 620; the guide rod 630 slides through the fixed base 610, the first end of the guide rod 630 is connected to the clamping assembly 200, the second end of the guide rod 630 is provided with the support platform 640, and the follower limiting member 400 is fixedly mounted on the support platform 640. It is understood that by installing the clamping assembly 200 on the telescopic rod of the lifting driver 620 mounted on the fixed base 610, the lifting driver 620 can drive the clamping assembly 200 to rise and fall. Furthermore, by allowing the guide rod 630 to slide through the fixed base 610, with its first end connected to the clamping assembly 200, the guide rod 630 can guide the rising and falling of the clamping assembly 200. Simultaneously, since the follower limiting member 400 is fixedly installed on the support platform 640 at the second end of the guide rod 630, the support platform 640 can drive the follower limiting member 400 to rise and fall smoothly. In this embodiment, the lifting driver 620 is a cylinder, and the fixed base 610 has a sliding hole 6101 through which the guide rod 630 slides.

[0046] Please see Figure 1 and Figure 3 In some embodiments, a retaining roller 3110 is rotatably mounted on the limiting member 310, and a buffer inclined edge 401 is formed on the follower limiting member 400. The retaining roller 3110 abuts against the buffer inclined edge 401 to determine the lifting height of the clamping assembly 200 within the height range of the lifting movement space 3202. It can be understood that by having the buffer inclined edge 401 formed on the follower limiting member 400 abut against the retaining roller 3110 rotatably mounted on the limiting member 310, the retaining roller 3110 rotates under the retaining force to absorb the impact force, thereby reducing the impact force on the limiting part. In this embodiment, when the lifting drive 620 is a cylinder, the limiting member 310 is a conventional limit switch. The limit switch is electrically connected to the valve of the lifting drive 620 to control the valve opening and closing, thereby controlling the lifting stroke of the lifting drive 620. This is prior art and will not be described in detail here.

[0047] Please see Figures 1 to 3This disclosure also provides a passenger aircraft assembly equipment, including the passenger aircraft component loading mechanism of any of the above embodiments. It is understood that by applying the aircraft component loading mechanism disclosed herein to aircraft assembly equipment, since the stroke measuring rod 320 installed on the frame 100 is parallel to the lifting path of the clamping assembly 200, and the stroke measuring rod 320 is provided with a reference position 3210 and at least two adjustment positions 3220 in sequence along the length direction, and a lifting space 3202 is formed between the limiting member 310 installed on the reference position 3210 and the limiting member 310 detachably installed on any one of the adjustment positions 3220, when the follower limiting member 400 moves synchronously with the clamping assembly 200 and rises and falls within the lifting space 3202, the follower limiting member 400 can respond to the lifting height of the clamping assembly 200, thereby limiting the lifting height of the follower limiting member 400 by partially abutting against the limiting member 310, thereby limiting the lifting height of the clamping assembly 200 within the height range of the lifting space 3202. In this way, the staff can adjust another limiting component 310 to the corresponding adjustment position 3220 according to the installation height of different components, and finally flexibly adjust the height range of the lifting and lowering space 3202 and control the lifting and lowering height of the clamping component 200.

[0048] Compared with the prior art, this disclosure has at least the following advantages:

[0049] The aforementioned passenger aircraft component loading mechanism, since the stroke measuring rod 320 installed on the frame 100 is parallel to the lifting path of the clamping assembly 200, and the stroke measuring rod 320 is provided with a reference position 3210 and at least two adjustment positions 3220 in sequence along the length direction, and a lifting space 3202 is formed between the limiting member 310 installed on the reference position 3210 and the limiting member 310 that can be detachably installed on any one of the adjustment positions 3220, when the follower limiting member 400 moves synchronously with the clamping assembly 200 and rises and falls within the lifting space 3202, the follower limiting member 400 can respond to the lifting height of the clamping assembly 200, thereby limiting the lifting height of the follower limiting member 400 by partially abutting against the limiting member 310, thereby limiting the lifting height of the clamping assembly 200 within the height range of the lifting space 3202. In this way, the staff can adjust another limiting component 310 to the corresponding adjustment position 3220 according to the installation height of different components, and finally flexibly adjust the height range of the lifting and lowering space 3202 and control the lifting and lowering height of the clamping component 200.

[0050] The embodiments described above are merely illustrative of several implementations of this disclosure, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of the utility model patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this disclosure, and these all fall within the protection scope of this disclosure. Therefore, the protection scope of this patent should be determined by the appended claims.

Claims

1. A passenger aircraft component loading mechanism, comprising: frame; A clamping assembly, which is elliptical and mounted on the frame, is used to clamp aircraft parts; The aircraft component loading mechanism is characterized in that it further includes a travel limiting component and a follow-up limiting component; The travel limiting component includes a travel measuring rod and two limiting components. The travel measuring rod is mounted on the frame. The travel measuring rod is parallel to the lifting path of the clamping component. A reference position and at least two adjustment positions are sequentially arranged along the length direction on the travel measuring rod. One of the limiting components is mounted on the reference position, and the other limiting component is detachably mounted on any of the adjustment positions. A lifting space is formed between the two adjustment positions. A follower limiting member is connected to the clamping component, and a portion of the follower limiting member is located within the lifting space. The follower limiting member is used to lift and lower with the clamping component, and a portion of the follower limiting member abuts against the limiting components to determine the lifting height of the clamping component within the height range of the lifting space.

2. The passenger aircraft component loading mechanism according to claim 1, characterized in that, The travel measuring rod is provided with an installation structure at each of the adjustment positions.

3. The passenger aircraft component loading mechanism according to claim 2, characterized in that, The mounting structure is a mounting hole, in which a threaded connector is installed, and the threaded connector is threadedly connected to the corresponding limiting component.

4. The passenger aircraft component loading mechanism according to claim 2, characterized in that, The installation structures are evenly spaced apart.

5. The passenger aircraft component loading mechanism according to claim 1, characterized in that, The frame is also provided with a clamping rod assembly, which includes a mounting base and a cover plate stacked on top of each other. The mounting base is fixedly connected to the frame, and a portion of the stroke measuring rod is disposed between the mounting base and the cover plate. The cover plate is locked to the mounting base to clamp and fix a portion of the stroke measuring rod to the clamping rod assembly.

6. The passenger aircraft component loading mechanism according to claim 5, characterized in that, The travel measuring rod is provided with a guide waist-shaped groove, and the cover plate is provided with a mating boss protruding into the guide waist-shaped groove.

7. The passenger aircraft component loading mechanism according to claim 1, characterized in that, The aircraft component loading mechanism also includes a lifting assembly, which is mounted on the frame, and the clamping assembly is mounted on the telescopic end of the lifting assembly.

8. The passenger aircraft component loading mechanism according to claim 7, characterized in that, The lifting assembly includes a fixed base, a lifting drive, a guide rod, and a carrying platform; the fixed base is fixedly connected to the frame, the lifting drive is mounted on the fixed base, and the clamping assembly is mounted on the telescopic rod of the lifting drive; the guide rod slides through the fixed base, the first end of the guide rod is connected to the clamping assembly, the second end of the guide rod is provided with the carrying platform, and the follow-up limiting member is fixedly mounted on the carrying platform.

9. The passenger aircraft component loading mechanism according to claim 1, characterized in that, The limiting component is rotatably provided with a retaining roller, and the follower limiting component is formed with a buffer inclined edge; the retaining roller abuts against the buffer inclined edge to determine the lifting height of the clamping assembly within the height range of the lifting and lowering space.

10. A passenger aircraft assembly equipment, characterized in that, Includes the passenger aircraft component loading mechanism according to any one of claims 1 to 9.

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