Fastening tool for aircraft narrow area inner lock and aircraft maintenance device

Abstract

The present disclosure provides an aircraft narrow area locking fastening tool and an aircraft maintenance device; the aircraft narrow area locking fastening tool comprises a clamping piece, a pressing piece, a closing spring and a wedge; the clamping piece and the pressing piece are oppositely arranged; a self-adapting clamping groove is formed in the first end of the clamping piece; the flexible end of the pressing piece is connected to the clamping piece, and the flexible end of the pressing piece is arranged away from the self-adapting clamping groove; the rigid end of the pressing piece is opposite to the self-adapting clamping groove; the wedge and the closing spring are located between the clamping piece and the pressing piece; the closing spring is connected to the clamping piece and the pressing piece respectively, so that the clamping piece and the pressing piece are closed; the wedge is slidably abutted to the clamping piece and the pressing piece respectively; the wedge has a wedge inclined surface; when the opening of the aircraft narrow area locking fastening tool needs to be adjusted, the wedge can be conveniently moved to overcome the elastic force, so that the clamping piece and the pressing piece are guided to open or close through the wedge inclined surface of the wedge.

Description

Technical Field

[0001] This disclosure relates to the technical field of aircraft maintenance, and in particular to a fastening tool for locking within a narrow area of ​​an aircraft and an aircraft maintenance device. Background Technology

[0002] To enhance comfort in first-class cabins, fasteners such as screws and bolts are installed in a concealed manner. During routine aircraft maintenance, these concealed fasteners may become loose, and these concealed locations are typically narrow, overlapping, and obstructed areas, making reinstallation extremely inconvenient. To address this issue, a fastener clamp for aircraft structural maintenance in confined spaces, as described in Chinese patent document CN218698432U, can clamp fasteners into concealed locations via a slot engaging with an elastic clamping piece. However, due to its structural design, the clamping space between the slot and the elastic clamping piece is very limited, and as the size of the fastener increases, the clamping space becomes insufficient to accommodate it. Utility Model Content

[0003] The purpose of this disclosure is to overcome the shortcomings of the prior art and to provide a fastening tool and aircraft maintenance device for clamping and installing locking components of different sizes in the narrow space of an aircraft.

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

[0005] A fastening tool for locking within a narrow area of ​​an aircraft, comprising a retaining piece and a pressing piece positioned opposite each other;

[0006] The aircraft narrow-area locking fastening tool also includes a pull spring and a wedge-shaped component;

[0007] The first end of the retaining piece has an adaptive groove for clamping the bolt of the locking member; the flexible end of the pressure plate is connected to the retaining piece and is located away from the adaptive groove; the rigid end of the pressure plate is opposite to the adaptive groove and is used to press the end cap of the locking member against the retaining piece; the wedge and the pull spring are located between the retaining piece and the pressure plate; the pull spring is connected to the retaining piece and the pressure plate respectively to bring the retaining piece and the pressure plate closer together; the wedge slides against the retaining piece and the pressure plate respectively; the wedge has a wedge-shaped inclined surface and is used to guide the retaining piece and the pressure plate to open or close together during movement.

[0008] In some embodiments, the wedge is slidably connected to the retaining piece, and the wedge slides against the pressure piece via the wedge-shaped inclined surface; the inclination angle of the wedge-shaped inclined surface is greater than the minimum included angle between the retaining piece and the pressure piece.

[0009] In some embodiments, the retaining piece has two limiting walls, and the wedge is disposed between the two limiting walls; each limiting wall has a guide groove; a portion of the wedge is slidably accommodated in the corresponding guide groove.

[0010] In some embodiments, the pressure plate protrudes toward the retaining plate and forms a wedge-shaped portion; the inclined surface of the wedge-shaped portion slides in contact with the inclined surface of the wedge.

[0011] In some embodiments, the wedge-shaped ramp is inclined toward the flexible end by the adaptive slot, and the wedge portion is located between the wedge and the flexible end.

[0012] In some embodiments, a locking block is formed on the retaining piece; the locking block is disposed on the sliding path of the wedge and is located on the side of the wedge opposite to the wedge portion.

[0013] In some embodiments, the adaptive card slot gradually expands from the inside out and is V-shaped.

[0014] In some embodiments, the wedge is slidably connected to the pressure plate, and the wedge slides against the retaining plate via a wedge-shaped inclined surface; the inclination angle of the wedge-shaped inclined surface is greater than the minimum included angle between the retaining plate and the pressure plate.

[0015] In some embodiments, the aircraft narrow-area locking fastening tool further includes a push-pull member, which includes a first pull arm, a pull handle, and a second pull arm connected in sequence. The first pull arm and the second pull arm are both perpendicular to the pull handle. The first pull arm is connected to a first side wall of the wedge-shaped member, and the second pull arm is connected to a second side wall of the wedge-shaped member.

[0016] An aircraft maintenance apparatus includes a fastening tool for locking within a narrow area of ​​an aircraft, as described in any of the above embodiments.

[0017] Compared with the prior art, this disclosure has at least the following advantages:

[0018] The aforementioned aircraft narrow-area locking fastening tool features an adaptive slot at the first end of the retaining plate, allowing it to adaptively hold the bolts of larger locking components. A flexible end on the pressure plate, positioned away from the adaptive slot, connects to the retaining plate, ensuring the connection point between them is further away from the slot. This flexible end allows for elastic deformation, resulting in a larger opening compared to existing technologies when the pressure plate and retaining plate are at the same angle. This allows the rigid end of the pressure plate and the retaining plate to accommodate the end caps of larger locking components. Furthermore, a pull spring pulls the retaining plate and pressure plate together, enabling the rigid end and retaining plate to clamp the locking component with elastic force, thus reducing the risk of the locking component falling off. Furthermore, since the wedge-shaped parts slide against the retaining plate and the pressure plate respectively, when it is necessary to adjust the opening of the fastening tool used for locking in the narrow area of ​​the aircraft, the elastic force can be easily overcome by moving the wedge-shaped parts, so as to guide the retaining plate and the pressure plate to open or close through the wedge-shaped inclined surface of the wedge-shaped parts. Attached Figure Description

[0019] 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.

[0020] Figure 1 This is a schematic diagram of the structure of a fastening tool for locking within a narrow area of ​​an aircraft according to an embodiment of the present disclosure;

[0021] Figure 2 for Figure 1 A cross-sectional view of the fastening tool used for locking within a narrow section of the aircraft, as shown;

[0022] Figure 3 for Figure 2 The cross-sectional view obtained by cutting along A1-A2.

[0023] Figure label:

[0024] 100. Holding piece; 101. Adaptive card slot; 110. Limiting wall; 1101. Guide groove; 120. Locking block;

[0025] 200, tablet compression; 210, flexible end; 220, rigid end; 230, wedge-shaped portion;

[0026] 300. Pulling spring;

[0027] 400. Wedge-shaped component; 410. Wedge-shaped inclined surface;

[0028] 500, Push-pull component; 510, First pull arm; 520, Pull handle; 530, Second pull arm;

[0029] 600. Locking component; 610. Bolt; 620. End cap. Detailed Implementation

[0030] 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.

[0031] 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.

[0032] 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.

[0033] To better understand the technical solutions and beneficial effects of this disclosure, the following detailed description is provided in conjunction with specific embodiments:

[0034] One embodiment of an aircraft narrow-area locking fastening tool includes a retaining plate 100, a pressure plate 200, a tension spring 300, and a wedge 400; the retaining plate 100 and the pressure plate 200 are positioned opposite each other; the first end of the retaining plate 100 has an adaptive groove 101 for clamping the bolt 610 of the locking member 600; the flexible end 210 of the pressure plate 200 is connected to the retaining plate 100 and is positioned away from the adaptive groove 101; the rigid end 220 of the pressure plate 200 is positioned opposite to the adaptive groove 101. The rigid end 220 of 200 is used to press the end cap 620 of the locking member 600 against the retaining piece 100; the wedge-shaped member 400 and the pull-close spring 300 are located between the retaining piece 100 and the pressure piece 200; the pull-close spring 300 is connected to the retaining piece 100 and the pressure piece 200 respectively, so that the retaining piece 100 and the pressure piece 200 come closer together; the wedge-shaped member 400 slides against the retaining piece 100 and the pressure piece 200 respectively; the wedge-shaped member 400 has a wedge-shaped inclined surface 410, which is used to guide the retaining piece 100 and the pressure piece 200 to open or close together during movement. The pull-close spring 300 is always in a stretched state.

[0035] It is understandable that, since the first end of the retaining piece 100 has an adaptive slot 101, it can adaptively retain the bolt 610 of the larger locking member 600 through the adaptive slot 101. Then, by connecting the flexible end 210 of the pressure piece 200, which is located away from the adaptive slot 101, to the retaining piece 100, the connection position between the pressure piece 200 and the retaining piece 100 is away from the adaptive slot 101, and the flexible end 210 can elastically deform. In this way, the pressure piece 200 and the retaining piece 100... Under the same included angle condition, the aforementioned aircraft narrow-area locking fastening tool has a larger opening compared to the prior art. This allows the rigid end 220 of the pressure plate 200 and the retaining plate 100 to accommodate the end cap 620 of the larger locking member 600. Furthermore, by pulling the retaining plate 100 and the pressure plate 200 together with the tension spring 300, the rigid end 220 and the retaining plate 100 can clamp the locking member 600 together through elastic force, thereby reducing the possibility of the locking member 600 falling off. Since the wedge 400 slides against the retaining plate 100 and the pressure plate 200 respectively, when it is necessary to adjust the opening of the aircraft narrow-area locking fastening tool, the elastic force can be easily overcome by moving the wedge 400, so that the retaining plate 100 and the pressure plate 200 can be guided to open or close through the wedge-shaped inclined surface 410 of the wedge 400.

[0036] In some embodiments, the pull spring 300 is fixedly connected to the retaining piece 100 and the pressure piece 200, respectively, and the flexible end 210 of the pressure piece 200 is fixedly connected to the retaining piece 100. Specifically, the above-mentioned fixed connection method can be welding.

[0037] Please see Figure 1 and Figure 2 In some embodiments, the wedge 400 is slidably connected to the retaining piece 100, and the wedge 400 slides against the pressure piece 200 via the wedge-shaped inclined surface 410; the inclination angle of the wedge-shaped inclined surface 410 is greater than the minimum included angle between the retaining piece 100 and the pressure piece 200. It can be understood that since the wedge 400 slides against the pressure piece 200 via the wedge-shaped inclined surface 410, and the wedge 400 is slidably connected to the retaining piece 100, and the inclination angle of the wedge-shaped inclined surface 410 is greater than the minimum included angle between the retaining piece 100 and the pressure piece 200, the minimum included angle between the retaining piece 100 and the pressure piece 200 is located near the flexible end 210. As the wedge 400 gradually approaches the flexible end 210, the pressure piece 200 can gradually open under the support of the wedge-shaped inclined surface 410.

[0038] Please see Figure 1 and Figure 2 In some embodiments, the pressure plate 200 protrudes towards the retaining piece 100, forming a wedge-shaped portion 230; the inclined surface of the wedge-shaped portion 230 slides against the wedge-shaped inclined surface 410. It can be understood that because the inclined surface of the wedge-shaped portion 230 on the pressure plate 200 slides against the wedge-shaped inclined surface 410 of the wedge-shaped member 400, the wedge-shaped portion 230 can slide relative to the wedge-shaped inclined surface 410 when the wedge-shaped member 400 moves, thereby adjusting the opening between the retaining piece 100 and the pressure plate 200.

[0039] Please see Figure 1 and Figure 2 In some embodiments, the wedge-shaped ramp 410 is inclined towards the flexible end 210 from the adaptive slot 101, and the wedge portion 230 is located between the wedge member 400 and the flexible end 210. It can be understood that because the wedge portion 230 is located between the wedge member 400 and the flexible end 210, and the wedge-shaped ramp 410 is inclined towards the flexible end 210 from the adaptive slot 101, the pressure plate 200 can gradually open under the support of the wedge-shaped ramp 410 as the wedge member 400 gradually approaches the flexible end 210. Specifically, the wedge-shaped ramp 410 is inclined downwards from the adaptive slot 101 towards the flexible end 210, and the vertical height of the surface of the wedge-shaped ramp 410 gradually decreases from the adaptive slot 101 towards the flexible end 210.

[0040] Please see Figure 2 and Figure 3In some embodiments, the retaining piece 100 has two limiting walls 110, and the wedge-shaped member 400 is disposed between the two limiting walls 110; each limiting wall 110 has a guide groove 1101; a portion of the wedge-shaped member 400 is slidably accommodated in the corresponding guide groove 1101. It can be understood that, since the wedge-shaped member 400 is disposed between the two limiting walls 110, and a portion of the wedge-shaped member 400 is slidably accommodated in the guide groove 1101 of the corresponding limiting wall 110, the sliding direction of the wedge-shaped member 400 can be limited by the guide groove 1101, allowing the wedge-shaped member 400 to slide more smoothly.

[0041] Please see Figure 1 and Figure 2 In some embodiments, a locking block 120 is formed on the retaining piece 100; the locking block 120 is disposed on the sliding path of the wedge member 400, and the locking block 120 is located on the side of the wedge member 400 opposite to the wedge portion 230. It can be understood that since the locking block 120 is disposed on the sliding path of the wedge member 400 and is located on the side of the wedge member 400 opposite to the wedge portion 230, the sliding formation of the wedge member 400 can be effectively restricted, reducing the occurrence of the inclined surface of the wedge portion 230 disengaging from the wedge inclined surface 410.

[0042] Please see Figure 1 In some embodiments, the adaptive slot 101 gradually expands from the inside out and is V-shaped. It can be understood that because the adaptive slot 101 gradually expands from the inside out to form a V-shape, the V-shaped slot structure can adapt to the bolts 610 of the locking member 600 of various sizes. Specifically, a serrated structure (not shown) is formed on the slot wall of the adaptive slot 101 to further enhance the holding effect on the bolts 610 of the locking member 600.

[0043] In other embodiments, the wedge is slidably connected to the pressure plate, and the wedge slides against the retaining plate via a wedge-shaped inclined surface; the inclination angle of the wedge-shaped inclined surface is greater than the minimum angle between the retaining plate and the pressure plate. It can be understood that because the wedge slides against the retaining plate via the wedge-shaped inclined surface, and the wedge is slidably connected to the pressure plate, the inclination angle of the wedge-shaped inclined surface is greater than the minimum angle between the retaining plate and the pressure plate. The minimum angle between the retaining plate and the pressure plate is located near the flexible end. As the wedge gradually moves closer to the flexible end, the pressure plate can gradually open under the support of the wedge-shaped inclined surface.

[0044] Please see Figure 1In some embodiments, the fastening tool for locking within a narrow area of ​​the aircraft further includes a push-pull member 500. The push-pull member 500 includes a first pull arm 510, a pull handle 520, and a second pull arm 530 connected in sequence. Both the first pull arm 510 and the second pull arm 530 are perpendicular to the pull handle 520. The first pull arm 510 is connected to the first sidewall of the wedge-shaped member 400, and the second pull arm 530 is connected to the second sidewall of the wedge-shaped member 400. It can be understood that because the first pull arm 510 is connected to the first sidewall of the wedge-shaped member 400, the second pull arm 530 is connected to the second sidewall of the wedge-shaped member 400, and the pull handle 520 is perpendicular to the first pull arm 510 and the second pull arm 530, the first sidewall and the second sidewall of the wedge-shaped member 400 can be pushed and pulled synchronously by driving the pull handle 520, thereby smoothly pushing and pulling the wedge-shaped member 400.

[0045] Please see Figures 1 to 3 This disclosure also provides an aircraft maintenance apparatus, including a fastening tool for locking within a narrow area of ​​an aircraft according to any of the above embodiments. It is understood that by applying the fastening tool for locking within a narrow area of ​​an aircraft according to this disclosure to an aircraft maintenance apparatus, since the first end of the retaining piece 100 has an adaptive slot 101, it can adaptively retain the bolt 610 of a larger locking member 600 through the adaptive slot 101. Then, by connecting the flexible end 210 of the pressure piece 200, which is located away from the adaptive slot 101, to the retaining piece 100, the connection point between the pressure piece 200 and the retaining piece 100 is located away from the adaptive slot 101, and the flexible end 210 can elastically... With deformation, under the condition that the pressure plate 200 and the retaining plate 100 are at the same included angle, the above-mentioned aircraft narrow-area locking fastening tool has a larger opening compared with the prior art. This allows the rigid end 220 of the pressure plate 200 and the retaining plate 100 to accommodate the end cap 620 of the larger locking member 600. Furthermore, by pulling the retaining plate 100 and the pressure plate 200 together with the tension spring 300, the rigid end 220 and the retaining plate 100 can clamp the locking member 600 together through elastic force, thereby reducing the possibility of the locking member 600 falling off. Since the wedge 400 slides against the retaining plate 100 and the pressure plate 200 respectively, when it is necessary to adjust the opening of the aircraft narrow-area locking fastening tool, the elastic force can be easily overcome by moving the wedge 400, so that the retaining plate 100 and the pressure plate 200 can be guided to open or close through the wedge-shaped inclined surface 410 of the wedge 400.

[0046] Compared with the prior art, this disclosure has at least the following advantages:

[0047] The aforementioned aircraft narrow-area locking fastening tool, because the first end of the retaining piece 100 has an adaptive retaining groove 101, can adaptively retain the bolt 610 of a larger locking member 600 through the adaptive retaining groove 101. Then, by connecting the flexible end 210 of the pressure piece 200, which is located away from the adaptive retaining groove 101, to the retaining piece 100, the connection position between the pressure piece 200 and the retaining piece 100 is away from the adaptive retaining groove 101, and the flexible end 210 can elastically deform. Thus, the pressure piece 200... With the clamping plate 100 and the clamping plate 200 at the same angle, the aforementioned aircraft narrow-area locking tool has a larger opening compared to the prior art. This allows the rigid end 220 of the pressure plate 200 and the clamping plate 100 to accommodate the end cap 620 of the larger locking member 600. Furthermore, by pulling the clamping plate 100 and the pressure plate 200 together with the tension spring 300, the rigid end 220 and the clamping plate 100 can clamp the locking member 600 together through elastic force, thereby reducing the possibility of the locking member 600 falling off. Since the wedge 400 slides against the clamping plate 100 and the pressure plate 200 respectively, when it is necessary to adjust the opening of the aircraft narrow-area locking tool, the elastic force can be easily overcome by moving the wedge 400, so that the clamping plate 100 and the pressure plate 200 can be guided to open or close through the wedge-shaped inclined surface 410 of the wedge 400.

[0048] 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 fastening tool for locking within a narrow area of ​​an aircraft, comprising a retaining plate and a pressing plate positioned opposite each other; Its features are, The aircraft narrow-area locking fastening tool also includes a pull spring and a wedge-shaped component; The first end of the retaining piece has an adaptive groove for clamping the bolt of the locking member; the flexible end of the pressure plate is connected to the retaining piece and is located away from the adaptive groove; the rigid end of the pressure plate is opposite to the adaptive groove and is used to press the end cap of the locking member against the retaining piece; the wedge and the pull spring are located between the retaining piece and the pressure plate; the pull spring is connected to the retaining piece and the pressure plate respectively to bring the retaining piece and the pressure plate closer together; the wedge slides against the retaining piece and the pressure plate respectively; the wedge has a wedge-shaped inclined surface and is used to guide the retaining piece and the pressure plate to open or close together during movement.

2. The fastening tool for locking within a narrow area of ​​an aircraft according to claim 1, characterized in that, The wedge-shaped member is slidably connected to the retaining piece, and the wedge-shaped member slides against the pressure piece through the wedge-shaped inclined surface; the inclination angle of the wedge-shaped inclined surface is greater than the minimum included angle between the retaining piece and the pressure piece.

3. The fastening tool for locking within a narrow area of ​​an aircraft according to claim 2, characterized in that, Two limiting walls are formed on the retaining piece, and the wedge is disposed between the two limiting walls; a guide groove is formed on each limiting wall; a portion of the wedge is slidably accommodated in the corresponding guide groove.

4. The fastening tool for locking within a narrow area of ​​an aircraft according to claim 2, characterized in that, The pressing plate protrudes towards the holding plate and forms a wedge-shaped portion; the inclined surface of the wedge-shaped portion slides and fits against the inclined surface of the wedge.

5. The fastening tool for locking within a narrow area of ​​an aircraft according to claim 4, characterized in that, The wedge-shaped inclined surface is inclined towards the flexible end from the adaptive slot, and the wedge-shaped part is located between the wedge-shaped member and the flexible end.

6. The fastening tool for locking within a narrow area of ​​an aircraft according to claim 4, characterized in that, A locking block is formed on the retaining piece; the locking block is disposed on the sliding path of the wedge-shaped member, and the locking block is located on the side of the wedge-shaped member opposite to the wedge-shaped portion.

7. The fastening tool for locking within a narrow area of ​​an aircraft according to claim 1, characterized in that, The adaptive card slot gradually expands from the inside out and is V-shaped.

8. The fastening tool for locking within a narrow area of ​​an aircraft according to claim 1, characterized in that, The wedge-shaped member is slidably connected to the pressure plate, and the wedge-shaped member slides against the retaining plate through the wedge-shaped inclined surface; the inclination angle of the wedge-shaped inclined surface is greater than the minimum included angle between the retaining plate and the pressure plate.

9. The fastening tool for locking within a narrow area of ​​an aircraft according to claim 1, characterized in that, The aircraft narrow-area locking fastening tool also includes a push-pull component, which includes a first pull arm, a pull handle, and a second pull arm connected in sequence. The first pull arm and the second pull arm are both perpendicular to the pull handle. The first pull arm is connected to the first side wall of the wedge-shaped component, and the second pull arm is connected to the second side wall of the wedge-shaped component.

10. An aircraft maintenance device, characterized in that, The fastening tool for locking within a narrow area of ​​an aircraft, as described in any one of claims 1 to 9.

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