Airplane pneumatic profile detection device

Abstract

The invention discloses an aircraft pneumatic profile detection device, which belongs to the technical field of aircraft pneumatic profile detection, and comprises a support underframe, and the top end of the support underframe is provided with two symmetrically arranged first sliding seats and two symmetrically arranged second sliding seats. Sliding grooves matched with the first sliding base and the second sliding base are formed in the periphery of the top end of the supporting bottom frame. According to the aircraft pneumatic profile detection device, when the aircraft pneumatic profile detection device is used and the position of the first sliding seat is adjusted, the spline sleeve can be pulled to move in the direction away from the second fluted disc on the outer side of the spline bar and the outer side of the rotating shaft, the first fluted disc is driven to be away from clamping with the second fluted disc, and then the rotating shaft can be driven to rotate through the handle; and then the worm gear lead screw lifting structure is operated to adjust the height of the supporting plate, at the moment, the first sliding seat can be moved to adjust the position, after adjustment is completed, the spline housing is released, and the first fluted disc is clamped on the second fluted disc again under the reverse action of the elastic piece.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft aerodynamic profile detection, and particularly relates to an aircraft aerodynamic profile detection device. Background Art

[0002] An aircraft is an aircraft that flies within the atmosphere and uses the lift generated by the air to balance its own gravity, and uses various aerodynamic forces to control its flight. Therefore, whether the aircraft aerodynamic profile meets the requirements of the original design has a crucial impact on the flight performance and flight safety of the aircraft. Among them, the aircraft aerodynamic profile mainly includes the wing aerodynamic profile and the fuselage aerodynamic profile, etc.

[0003] For the aircraft aerodynamic profile detection device with the authorization announcement number of CN112797872A, including a clamping structure and an inspection template. Among them, the support frame and the clamping structure are both arranged above the base and their positions are adjustable. The support frame has at least two, which are used to support the aircraft or parts to be detected. The clamping structures are arranged in pairs and oppositely, which are used to clamp the inspection template. The inspection templates are arranged in pairs and are respectively fixed on the clamping structures. An opening matching the aerodynamic profile of the position to be detected is arranged on the inspection template, and a measurement buffer strip is arranged on the inner circumference of the opening. This aircraft aerodynamic profile detection device has a reasonable structure, can be adjusted according to the aircraft or parts to be detected to adapt to the detection of different structures and different positions, and can also realize the batch inspection of the structures to be detected with the same specifications and models.

[0004] Although the above application can realize the adjustment and change of the position of the longitudinal beam or the support frame by fixing the connecting angle piece with screws, due to external factors, the handwheel end of the worm screw lifting structure will rotate accidentally, resulting in the influence on the stability during detection support, and the accidental rotation will cause the positioning position of the template to be detected to change, thus affecting the accuracy of the detection result. Therefore, an aircraft aerodynamic profile detection device is needed. Summary of the Invention

[0005] The purpose of the present invention is to provide an aircraft aerodynamic profile detection device to solve the problems put forward in the above background art.

[0006] To achieve the above object, the present invention provides the following technical solution: An aircraft aerodynamic profile detection device, comprising a support chassis, at the top of the support chassis are provided two symmetrically arranged first sliding seats and two symmetrically arranged second sliding seats, around the top of the support chassis are respectively opened sliding grooves adapted to the first sliding seats and the second sliding seats, on each of the first sliding seats is connected with a support plate through a worm screw lifting structure, at the top of each of the second sliding seats is fixedly connected with a vertical rod, in the sliding grooves opened on the vertical rod are slidably connected third sliding seats, on each of the third sliding seats is connected with a clamping plate through a worm screw lifting structure, the worm screw lifting structures on the first sliding seats are all connected with a locking component between the first sliding seats, and the worm screw lifting structures on the third sliding seats are also all connected with a locking component between the vertical rods; a synchronization component, the synchronization component is installed on the vertical rods and is adapted to the locking components on the third sliding seats.

[0007] As a preferred embodiment, the locking component includes a rotating shaft provided on the worm screw lifting structure on the first sliding seat or the third sliding seat, on the outer side of the rotating shaft is fixedly connected with a key strip, slidably sleeved on the outer sides of the rotating shaft and the key strip is a spline sleeve with a convex cross-sectional structure, on the outer side of the spline sleeve is fixedly connected with a first gear disk, the first gear disk is engaged with a second gear disk, the second gear disk is fixedly connected to the outer side of the worm screw lifting structure, at one end of the spline sleeve away from the second gear disk are movably inserted a plurality of first inserts arranged in an annular array, on the outer sides of the first inserts are fixedly connected with the same second insert through two symmetrically arranged elastic pieces.

[0008] As a preferred embodiment, at one end of the rotating shaft away from the second gear disk is fixedly connected with a handle, and the second inserts are all movably inserted into the handle.

[0009] As a preferred embodiment, the cross-sectional structure of the elastic piece is a V-shaped structure, and a weakening groove is opened in the middle of the elastic piece.

[0010] As a preferred embodiment, an annular groove is opened on the periphery of the first gear disk, slidably connected in the annular groove is a guide block with a convex cross-sectional structure, the guide block is in an arc shape structure, on the outer side of the guide block is fixedly connected with a toothed plate, the toothed plate is slidably sleeved on the outer side of a first guide rod, and one end of the first guide rod is fixedly connected to the outer side of the first sliding seat or the third sliding seat.

[0011] As a preferred embodiment, the toothed plate is engaged with the outer sides of a plurality of equidistantly arranged teeth, and the plurality of teeth are fixedly connected to the outer wall of the support chassis or the outer wall of the vertical rod;

[0012] As a preferred embodiment, the synchronization component includes two symmetrically arranged second guide rods fixedly connected to the outer wall of the vertical rod. A synchronization plate with a C-shaped cross-section in the vertical direction is slidably sleeved outside the two second guide rods. The cross-section of the synchronization plate is also C-shaped, and the synchronization plate is fixedly connected to the outside of the vertical rod through two springs.

[0013] As a preferred embodiment, at one end of the toothed plate close to the synchronization plate and fitting against the outside of the synchronization plate, a first inclined surface is provided, and a second inclined surface cooperating with the first inclined surface is provided on the synchronization plate.

[0014] As a preferred embodiment, at the bottom of the synchronization plate and on a side wall facing the inner wall of the support chassis, a positioning post is fixedly connected, and a positioning hole cooperating with the positioning post is provided on the inner wall of the support chassis.

[0015] Compared with the prior art, an aircraft aerodynamic profile detection device provided by the present invention has at least the following beneficial effects:

[0016] In the present invention, when using the aircraft aerodynamic profile detection device, when adjusting the position of the first sliding seat, the spline sleeve can be pulled to cause the spline sleeve to move away from the second gear disk on the outside of the key bar and the rotating shaft. The first gear disk is driven away from the engagement with the second gear disk, so that the rotating shaft can be rotated by the handle, and then the worm screw lifting structure is operated to adjust the height of the support plate. At this time, the first sliding seat can also be moved to adjust the position. After the adjustment is completed, release the spline sleeve. Under the reverse action of the elastic piece, when the first gear disk is re-engaged with the second gear disk, the toothed plate is driven to engage with multiple teeth, realizing the fixation of the position of the first sliding seat and fixing and limiting the rotating shaft, thereby avoiding the problem that the handwheel rotates due to the activities of personnel during external detection and affecting the stability of the detection template. Secondly, when the spline sleeve on the third sliding seat is pulled, the toothed plate is driven to disengage from multiple teeth, and with the extrusion of the first inclined surface against the second inclined surface, the synchronization plate moves on the second guide rod, drives the spring to stretch, and the positioning post disengages from the positioning hole. In this way, after adjusting the up and down position of the third sliding seat on the vertical rod, the position adjustment of the vertical rod and the fixation of the rotating shaft are both realized through the cooperation of the locking component and the synchronization component, so that it is not necessary to adjust and fix its position by disassembling and assembling screws, making the adjustment and fixation more convenient and fast, greatly improving the detection efficiency, and being able to facilitate the adjustment of the position according to different templates to be detected. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a three-dimensional first perspective structural schematic diagram of the whole of the present invention;

[0018] Figure 2Schematic diagram of the overall three-dimensional second perspective of the present invention;

[0019] Figure 3 Schematic diagram of the overall three-dimensional third perspective of the present invention;

[0020] Figure 4 Schematic diagram of the overall top view plane structure of the present invention;

[0021] Figure 5 Schematic diagram of the enlarged structure at position A of the present invention;

[0022] Figure 6 Schematic diagram of the enlarged structure at position B of the present invention;

[0023] Figure 7 Schematic diagram of the enlarged structure at position C of the present invention.

[0024] In the figure: 1, support chassis; 11, first sliding seat; 12, rotating shaft; 2, worm screw lifting structure; 21, support plate; 3, second sliding seat; 31, vertical rod; 32, third sliding seat; 4, locking component; 41, key bar; 42, spline sleeve; 421, first tooth disc; 44, second tooth disc; 45, first insert block; 46, elastic piece; 47, weakening groove; 48, handle; 49, second insert block; 410, annular groove; 411, guide block; 412, toothed plate; 413, first guide rod; 414, teeth; 5, synchronization component; 51, first inclined surface; 52, synchronization plate; 53, second guide rod; 54, spring; 55, positioning column; 56, positioning hole; 6, clamping plate. Detailed implementation manners

[0025] The following further describes the present invention in conjunction with embodiments.

[0026] In order to make the objectives, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings of the embodiments of the present invention. Obviously, the described embodiments are some but not all of the embodiments of the present invention. Based on the described embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts fall within the scope of protection of the present invention.

[0027] The following embodiments are used to illustrate the present invention, but cannot be used to limit the scope of protection of the present invention. The conditions in the embodiments can be further adjusted according to specific conditions. Any simple improvement to the method of the present invention under the premise of the concept of the present invention falls within the scope of protection required by the present invention.

[0028] Embodiment

[0029] Although the above application can adjust and change the position of the longitudinal beam or the support frame by fixing the connecting angle piece with screws, due to external factors, the handwheel end of the worm screw lifting structure 2 will rotate accidentally, resulting in the instability during the detection support, and the accidental rotation will cause the positioning position of the template to be detected to change, thus affecting the accuracy of the detection result;

[0030] Therefore, please refer to Figures 1-5 , the present invention provides an aircraft aerodynamic profile detection device, including: a support chassis 1, two symmetrically arranged first sliding seats 11 and two symmetrically arranged second sliding seats 3 are provided at the top of the support chassis 1, sliding grooves matching with the first sliding seats 11 and the second sliding seats 3 are respectively opened around the top of the support chassis 1, a support plate 21 is connected to each of the first sliding seats 11 through a worm screw lifting structure 2, vertical rods 31 are fixedly connected to the tops of the second sliding seats 3, third sliding seats 32 are slidably connected to the sliding grooves opened on the vertical rods 31, a clamping plate 6 is connected to each of the third sliding seats 32 through a worm screw lifting structure 2, a locking component 4 is connected between the worm screw lifting structure 2 on each of the first sliding seats 11 and the first sliding seat 11, and a locking component 4 is also connected between the worm screw lifting structure 2 on each of the third sliding seats 32 and the vertical rod 31; a synchronization component 5, the synchronization component 5 is installed on the vertical rod 31 and is matched with the locking component 4 on the third sliding seat 32.

[0031] Furthermore, as shown in Figures 1-7As shown, it is worth specifically explaining that in order to enable the sliding seat to be locked in position after moving and adjusting, and to enable the rotating shaft 12 to be fixed simultaneously, the locking assembly 4 is provided with a rotating shaft 12 on the worm screw lifting structure 2 on the first sliding seat 11 or the third sliding seat 32. A key bar 41 is fixedly connected to the outer side of the rotating shaft 12. A spline sleeve 42 with a convex cross-sectional structure is slidably sleeved on the outer sides of the rotating shaft 12 and the key bar 41. A first tooth disc 421 is fixedly connected to the outer side of the spline sleeve 42. The first tooth disc 421 is engaged with a second tooth disc 44. The second tooth disc 44 is fixedly connected to the outer side of the worm screw lifting structure 2. A plurality of first inserts 45 arranged in an annular array are movably inserted at one end of the spline sleeve 42 away from the second tooth disc 44. The outer sides of the first inserts 45 are fixedly connected to the same second insert 49 through two symmetrically arranged elastic pieces 46. A handle 48 is fixedly connected to one end of the rotating shaft 12 away from the second tooth disc 44. The second inserts 49 are all movably inserted into the handle 48. The cross-section of the elastic piece 46 is in a V-shaped structure, and a weakening groove 47 is provided in the middle of the elastic piece 46. An annular groove 410 is provided on the periphery of the first tooth disc 421. A guide block 411 with a convex cross-sectional structure is slidably connected in the annular groove 410. The guide block 411 is in an arc-shaped structure. A toothed plate 412 is fixedly connected to the outer side of the guide block 411. The toothed plate 412 is slidably sleeved on the outer side of the first guide rod 413. One end of the first guide rod 413 is fixedly connected to the outer side of the first sliding seat 11 or the third sliding seat 32. The toothed plate 412 is engaged with the outer sides of a plurality of equally spaced teeth 414. The plurality of teeth 414 are fixedly connected to the outer wall of the support chassis 1 or the outer wall of the vertical rod 31.

[0032] The setting of the annular groove 410 enables the first tooth disc 421 to rotate on the outer side of the guide block 411 when it rotates. When the first tooth disc 421 is manually pulled through the spline sleeve 42 and moves away from the second tooth disc 44, the presence of the guide block 411 makes the toothed plate 412 also move away from the plurality of teeth 414. Through the setting of the first inserts 45 and the second inserts 49, the elastic pieces 46 are convenient to be removed and replaced.

[0033] Furthermore, as Figures 1-7As shown, it is worth specifically noting that in order to enable the position of the vertical rod 31 to be fixed and cooperate with the above-mentioned locking assembly 4, a synchronization assembly 5 is provided, which includes two symmetrically arranged second guide rods 53 fixedly connected to the outer wall of the vertical rod 31. A synchronization plate 52 with a C-shaped cross-section in the vertical direction is slidably sleeved on the outer sides of the two second guide rods 53. The cross-section of the synchronization plate 52 is also C-shaped. The synchronization plate 52 is fixedly connected to the outside of the vertical rod 31 through two springs 54. At one end of the tooth plate 412 close to the synchronization plate 52 and fitting against the outer side of the synchronization plate 52, a first inclined surface 51 is provided. A second inclined surface is provided on the synchronization plate 52 to cooperate with the first inclined surface 51. At the bottom of the synchronization plate 52 and on the side wall facing the inner wall of the support chassis 1, a positioning post 55 is fixedly connected. A positioning hole 56 is provided on the inner wall of the support chassis 1 to cooperate with the positioning post 55.

[0034] Among them, when the tooth plate 412 moves in a direction away from the multiple teeth 414 and moves on the first guide rod 413, the first inclined surface 51 will squeeze the second inclined surface on the synchronization plate 52, causing the synchronization plate 52 to move on the two second guide rods 53 and stretch the two springs 54, and causing the positioning post 55 to be withdrawn from the positioning hole 56, thereby facilitating the adjustment of the position of the vertical rod 31.

[0035] In summary, when using the aircraft aerodynamic profile detection device, when adjusting the position of the first sliding seat 11, the spline sleeve 42 can be pulled to cause the spline sleeve 42 to move away from the second gear disc 44 on the outside of the key bar 41 and the rotating shaft 12. The first gear disc 421 is driven away from the engagement with the second gear disc 44, so that the rotating shaft 12 can be rotated through the handle 48, and then the worm screw lifting structure 2 is operated to adjust the height of the support plate 21. At this time, the first sliding seat 11 can also be moved to adjust the position. After the adjustment is completed, the spline sleeve 42 is released. Under the reverse action of the elastic piece 46, when the first gear disc 421 is re-engaged with the second gear disc 44 and drives the toothed plate 412 to be engaged with a plurality of teeth 414, while fixing the position of the first sliding seat 11, the rotating shaft 12 is fixed and limited, thus avoiding the problem that the handwheel rotates due to the movement of personnel during external detection and affecting the stability of the detection template. Secondly, when the spline sleeve 42 on the third sliding seat 32 is pulled, and the toothed plate 412 is driven to disengage from a plurality of teeth 414, and in cooperation with the extrusion of the first inclined surface 51 on the second inclined surface, the synchronous plate 52 moves on the second guide rod 53, and drives the spring 54 to be stretched, and the positioning column 55 disengages from the positioning hole 56. In this way, after the third sliding seat 32 on the vertical rod 31 adjusts the up and down position, the position adjustment of the vertical rod 31 and the fixation of the rotating shaft 12 are both realized through the cooperation of the locking component 4 and the synchronous component 5, so that it is not necessary to disassemble and assemble screws to adjust and fix its position, making the adjustment and fixation more convenient and fast, greatly improving the detection efficiency, and being able to facilitate the adjustment of the position according to different templates to be detected.

[0036] Unless otherwise defined, the technical terms or scientific terms used in the present invention shall have the ordinary meanings understood by those of ordinary skill in the art to which the present invention pertains. The terms "including" or "comprising" and the like used in the present invention mean that the elements or objects appearing before the term cover the elements or objects listed after the term and their equivalents, without excluding other elements or objects. The terms "connected" or "coupled" and the like are not limited to physical or mechanical connections, and may also include electrical connections, whether direct or indirect. The terms "upper", "lower", "left", "right" and the like are only used to represent relative positional relationships. When the absolute position of the object being described changes, the relative positional relationship may also change accordingly.

[0037] Although the embodiments of the present invention have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An aircraft aerodynamic surface detection device, comprising a support chassis (1). At the top of the support chassis (1), there are two symmetrically arranged first sliding seats (11) and two symmetrically arranged second sliding seats (3). Sliding grooves matching the first sliding seats (11) and the second sliding seats (3) are respectively formed around the top of the support chassis (1). On each of the first sliding seats (11), a support plate (21) is connected through a worm screw lifting structure (2). At the top of each of the second sliding seats (3), a vertical rod (31) is fixedly connected. A third sliding seat (32) is slidably connected in the sliding groove formed on the vertical rod (31). On each of the third sliding seats (32), a clamping plate (6) is connected through a worm screw lifting structure (2), characterized in that, A locking component (4) is connected between each worm screw lifting structure (2) on the first sliding seat (11) and the first sliding seat (11), and a locking component (4) is also connected between each worm screw lifting structure (2) on the third sliding seat (32) and the vertical rod (31). A synchronization component (5) is installed on the vertical rod (31) and is matched with the locking component (4) on the third sliding seat (32).

2. The aircraft aerodynamic surface detection device according to claim 1, characterized in that: The locking component (4) includes a rotating shaft (12) arranged on the worm screw lifting structure (2) on the first sliding seat (11) or the third sliding seat (32). A key bar (41) is fixedly connected to the outer side of the rotating shaft (12). A spline sleeve (42) with a convex cross-section is slidably sleeved on the outer sides of the rotating shaft (12) and the key bar (41). A first gear disk (421) is fixedly connected to the outer side of the spline sleeve (42). The first gear disk (421) is engaged with a second gear disk (44). The second gear disk (44) is fixedly connected to the outer side of the worm screw lifting structure (2). A plurality of first insertion blocks (45) arranged in an annular array are movably inserted at one end of the spline sleeve (42) away from the second gear disk (44). The outer sides of the first insertion blocks (45) are fixedly connected to the same second insertion block (49) through two symmetrically arranged elastic pieces (46).

3. The aircraft aerodynamic profile detection device according to claim 2, wherein: A handle (48) is fixedly connected to one end of the rotating shaft (12) away from the second gear disk (44). The second insertion blocks (49) are all movably inserted into the handle (48).

4. The aircraft aerodynamic profile detection device according to claim 2, characterized in that: The cross-section of the elastic piece (46) is in a V-shaped structure, and a weakening groove (47) is formed in the middle of the elastic piece (46).

5. The aircraft aerodynamic surface detection device according to claim 2, characterized in that: An annular groove (410) is formed in the periphery of the first gear disk (421). A guiding block (411) with a convex cross-section is slidably connected in the annular groove (410). The guiding block (411) is in an arc-shaped structure. A toothed plate (412) is fixedly connected to the outer side of the guiding block (411). The toothed plate (412) is slidably sleeved on the outer side of a first guiding rod (413). One end of the first guiding rod (413) is fixedly connected to the outer side of the first sliding seat (11) or the third sliding seat (32).

6. The aircraft aerodynamic profile detection device according to claim 5, wherein: The toothed plate (412) is engaged with the outer sides of a plurality of equally spaced teeth (414). The plurality of teeth (414) are fixedly connected to the outer wall of the support chassis (1) or the outer wall of the vertical rod (31).

7. The aircraft aerodynamic profile detection device according to claim 6, characterized in that: The synchronization component (5) includes two symmetrically arranged second guiding rods (53) fixedly connected to the outer wall of the vertical rod (31). The outer sides of the two second guiding rods (53) are slidably sleeved with the same synchronization plate (52) with a C-shaped vertical cross-section. The cross-section of the synchronization plate (52) is also in a C-shaped structure. The synchronization plate (52) is fixedly connected to the outer side of the vertical rod (31) through two springs (54).

8. The aircraft aerodynamic profile detection device according to claim 7, wherein: One end of the toothed plate (412) close to the synchronous plate (52) and attached to the outer side of the synchronous plate (52) is provided with a first inclined surface (51), and the synchronous plate (52) is provided with a second inclined surface that cooperates with the first inclined surface (51).

9. The aircraft aerodynamic profile detection device according to claim 8, characterized in that: On the bottom of the synchronous plate (52) and on a side wall facing the inner wall of the support chassis (1), a positioning post (55) is fixedly connected, and a positioning hole (56) that cooperates with the positioning post (55) is provided on the inner wall of the support chassis (1).

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