Aircraft spanwise beam fixing tool and fixing method

Abstract

The invention relates to the technical field of aircraft manufacturing, and discloses an aircraft spanwise beam fixing tool and method, and the tool mainly comprises a base, a screw rod, a rotating shaft, a linear guide rail, a rotating handle, a joint, a coupling mechanism, a male / female joint and the like. The fixing method comprises the steps that the tool is fixed to the tool by adjusting the ejector block and the jackscrew through the rotating handle on the base, the angle and height of the connecting mechanism are adjusted by rotating the round pipe, the male head on the aircraft spanwise beam and the female head of the tool are connected, and after preliminary fixing, the base handle is rotated to further adjust the position and height. The method has the advantages of simple and fast operation, firm and reliable fixation, spanwise beam surface protection, installation precision improvement and the like.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft manufacturing, and in particular to an aircraft span-wise beam fixing tool and a fixing method. Background Art

[0002] In the modern aviation industry, the aircraft span beam is an important part of the aircraft structure. Its installation accuracy and fixation reliability directly affect the overall performance and safety of the aircraft.

[0003] At present, there are many disadvantages in the traditional aircraft span beam fixing method. On the one hand, the existing fixing tools are complicated to operate, and require multiple steps and a long time to complete the fixing, which seriously affects the efficiency of aircraft manufacturing. On the other hand, these tools often cannot ensure the position accuracy of the span beam during the fixing process, and are prone to deviations, which brings difficulties to the subsequent assembly work. In addition, some fixing tools are prone to damage to the surface of the span beam, affecting the appearance quality and structural strength of the aircraft. Therefore, there is an urgent need for a new type of aircraft span beam fixing tool to solve the problems existing in the prior art. Summary of the invention

[0004] The object of the present invention is to provide a tool and method for fixing an aircraft span-wise beam, aiming to achieve efficient, accurate and safe fixing of the aircraft span-wise beam.

[0005] A first aspect of the present invention provides an aircraft span-wise beam fixing tool, comprising: a base mechanism 1, a connecting mechanism 2, and a joint mechanism 3;

[0006] The connecting mechanism 2 includes: a first rotating circular tube 14, a second rotating circular tube 15, a first threaded rod 17, and a second threaded rod 18; two ends of the second rotating circular tube 15 are respectively threadedly connected to the first threaded rod 17 and the second threaded rod 18;

[0007] The joint mechanism 3 comprises: a female joint 22, a ring 23, a male joint 24 and a rotating shaft 25;

[0008] The base mechanism 1 is arranged on two adjacent long stringers of the wing, the first ends of the first rotating circular tube 14 and the second threaded rod 18 are hinged on the base mechanism 1, and the second ends of the first rotating circular tube 14 are slidably connected to the second rotating circular tube 15;

[0009] One end of the female connector 22 is rotatably connected to the non-threaded end of the connecting rod 17 through a rotating shaft 25; the male connector 24 passes through the hole at the thin wall of the "I" structure of the span beam and is threadedly connected to the female connector 22, and rings 23 are padded on both sides of the span beam.

[0010] Optionally, the base mechanism 1 includes: a stopper 4, a fourth rotating screw 5, a first rotating handle 6, a universal support foot 7, a second rotating handle 8, a base 9, a first linear guide rail 10, a third rotating handle 11, a second linear guide rail 12 and a support 13;

[0011] The two ends of the base 9 are arranged above two adjacent long girders of the wing, and a first screw structure is arranged on the outer side of the first end of the base 9, which abuts against the outer side of the long girders, and the position of the base 9 relative to the long girders can be adjusted;

[0012] A stopper 4 is arranged on the outer side of the second end of the base 9, and a first linear guide rail 10 is arranged on the base 9. The stopper 4 is sleeved on the first linear guide rail 10 and connected to the base 9 through a second screw structure. The second rotating handle 8 is used to adjust the second screw structure. By rotating the second rotating handle 8, the stopper 4 is driven to slide on the first linear guide rail 10, thereby adjusting the distance between the stopper 4 and the base 9;

[0013] A support 13 is provided at the first end of the base 9 and below the stopper 4. The support 13 is located below the flange of the long rod. A guide rod is provided on the support 13. A second linear guide rail 12 is provided at the first end of the base 9 and inside the stopper 4. The guide is provided inside the second linear guide rail 12.

[0014] The first end of the base 9 is connected to the support 13, and the stopper 4 is connected to the support 13 through a third screw structure. The third rotating handle 11 is used to adjust the third screw structure. By rotating the third rotating handle 11, the support 13 slides on the second linear guide rail 12, thereby adjusting the distance between the support 13 and the first end of the base 9, and the distance between the support 13 and the stopper 4, so that the base 9 and the support 13 are clamped on the flange of the long stringer;

[0015] The two ends of the stopper 4 are also provided with a fourth rotating screw 5, and the two ends of the fourth rotating screw 5 are also provided with a first rotating handle 6 and a universal support foot 7;

[0016] The universal support foot 7 rests against the aircraft span beam.

[0017] Optionally, threaded holes are provided at both ends of the second rotating circular tube 15, and the first threaded rod 17 and the second threaded rod 18 are threadedly connected in the threaded holes, and the length of the connecting mechanism 2 is adjusted by adjusting the depth of the first threaded rod 17 and the second threaded rod 18 screwed into the threaded holes.

[0018] Optionally, the connecting mechanism 2 further includes: a round tube 16, a connecting piece 19, a rotating handle 20 and a connecting rod 21;

[0019] The round tube 16 is sleeved on the outside of the second rotating round tube 15, and the connecting piece 19 is sleeved on the outside of the round tube 16;

[0020] The second end of the first rotating circular tube 14 is connected to the connecting member 19 through a connecting rod 21. A rotating handle 20 is provided on the connecting member 19. The connecting member 19 is clamped or loosened by rotating the rotating handle 20 to control the sliding of the circular tube 16 on the second rotating circular tube 15, thereby controlling the angle of the connecting rod 21, and further controlling the length and angle of the entire connecting mechanism 2.

[0021] Optionally, a first end of the first rotating circular tube 14 is threadedly connected to a second threaded rod 18 , and the second threaded rod 18 is connected to the base mechanism 1 .

[0022] Optionally, the ring 23 is made of plastic.

[0023] Optionally, one end of the male connector 24 facing the female connector 22 is a φ30 step and an M12 thread.

[0024] A second aspect of the present invention provides a method for fixing an aircraft span-wise beam, using the aircraft span-wise beam fixing tool as described in any one of the first aspects, and the aircraft span-wise beam fixing method comprises:

[0025] The base mechanism 1 is arranged on two adjacent long spars of the wing, and the relative positions of the base 9, the stopper 4 and the support 13 are adjusted by adjusting the first rotating handle 6 and the second rotating handle 8 to perform pre-positioning;

[0026] Adjust the telescopic length and angle of the connecting rod of the coupling mechanism 2 so that the female joint 22 and the male joint 24 on the span beam are at the same height, and lock the coupling mechanism 2;

[0027] Connect the female connector 22 to the male connector 24 on the aircraft span beam to ensure tightness;

[0028] The first rotating handle 6 and the second rotating handle 8 are adjusted to fix the base 9 on the long stringer to ensure that it cannot be moved.

[0029] The present invention provides an aircraft span beam fixing tool and fixing method, which have the following beneficial effects:

[0030] (1) Easy and quick operation: The function of fixing and loosening the axial beam can be easily achieved through the connection method of male and female heads, which greatly improves work efficiency.

[0031] (2) Firm and reliable fixation: The precise fit between the male and female heads can provide sufficient fixing force to ensure that the span-wise beam will not move during installation.

[0032] (3) Protect the span-wise beam surface: The fixed-position male and female connection method prevents the friction caused by the movement of the support parts from damaging the span-wise beam surface of the aircraft, thereby ensuring the appearance quality and structural strength of the aircraft.

[0033] (4) Improve installation accuracy: Through the guide rail movement of the base and the precise male / female head connection, the position of the span beam can be quickly determined and fine-tuned, thereby improving installation accuracy. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 This is a schematic diagram of the structure of the span-wise beam fixing tool;

[0035] Figure 2 is a schematic diagram of the base structure;

[0036] Figure 3 It is a schematic diagram of the vertical structure of the base;

[0037] Figure 4 is a schematic diagram of the connection mechanism;

[0038] Figure 5 It is a schematic diagram of the male and female joint structure;

[0039] Figure 6 is a schematic diagram of the base structure;

[0040] Description of reference numerals:

[0041] 1 base mechanism, 2 connecting mechanism, 3 joint mechanism, 4 stopper, 5 fourth rotating screw, 6 first rotating handle, 7 universal support foot, 8 second rotating handle, 9 base, 10 first linear guide, 11 third rotating handle, 12 second linear guide, 13 support, 14 first rotating round tube, 15 second rotating round tube, 16 round tube, 17 first threaded rod, 18 second threaded rod, 19 connecting piece, 20 fourth rotating handle, 21 connecting rod, 22 female joint, 23 ring, 24 male joint, 25 rotating shaft. DETAILED DESCRIPTION

[0042] The present application is further described in detail below with reference to examples and drawings:

[0043] The invention provides an aircraft span-wise beam fixing tool and a fixing method. The aircraft span-wise beam fixing tool is mainly composed of a base, a screw rod, a rotating shaft, a linear guide rail, a rotating handle, a joint, a connecting mechanism, a male / female joint and other devices.

[0044] Base: The horizontal and longitudinal positions of the top block can be controlled by adjusting the position of the top block through the screw. The base is composed of a support, a rotating handle, a screw, a linear guide, a support foot, a top block, a nut, etc. It can be moved and locked on the tooling guide rail, which can effectively prevent the tool from sliding during the fixing process. The size of the base has been carefully designed to meet the needs of different working environments.

[0045] Connecting mechanism: The bottom is connected to the base, which is connected by 3 round tubes through connectors and connecting rods. The height and angle of the upper end can be adjusted by telescoping and rotating to achieve changes in the overall height and angle of the tool.

[0046] Male / female connector: One end of the male connector is connected to the upper end of the connecting mechanism, and the other end is connected to the female connector on the aircraft span beam, which plays the role of fixing and supporting the aircraft span beam. The female connector is fixed on the aircraft span beam to ensure that the tool and the aircraft span beam are fixed in the accurate position.

[0047] When in use, adjust the position of the tool base through the top screw and tighten it, adjust the height and angle through the round tube of the connecting mechanism and tighten the bolts to connect the male connector of the tool with the female connector of the aircraft span beam, so as to achieve the purpose of fixing and supporting the aircraft span beam.

[0048] like Figure 1 As shown in FIG. 6 , the present invention provides an aircraft span beam fixing tool, comprising: a base mechanism 1, a connecting mechanism 2, and a joint mechanism 3;

[0049] The connecting mechanism 2 includes: a first rotating circular tube 14, a second rotating circular tube 15, a first threaded rod 17, and a second threaded rod 18; two ends of the second rotating circular tube 15 are respectively threadedly connected to the first threaded rod 17 and the second threaded rod 18;

[0050] The joint mechanism 3 comprises: a female joint 22, a ring 23, a male joint 24 and a rotating shaft 25;

[0051] The base mechanism 1 is arranged on two adjacent long stringers of the wing, the first ends of the first rotating circular tube 14 and the second threaded rod 18 are hinged on the base mechanism 1, and the second ends of the first rotating circular tube 14 are slidably connected to the second rotating circular tube 15;

[0052] One end of the female connector 22 is rotatably connected to the non-threaded end of the connecting rod 17 through a rotating shaft 25; the male connector 24 passes through the hole at the thin wall of the "I" structure of the span beam and is threadedly connected to the female connector 22, and rings 23 are padded on both sides of the span beam.

[0053] Optionally, the base mechanism 1 includes: a stopper 4, a fourth rotating screw 5, a first rotating handle 6, a universal support foot 7, a second rotating handle 8, a base 9, a first linear guide rail 10, a third rotating handle 11, a second linear guide rail 12 and a support 13;

[0054] The two ends of the base 9 are arranged above two adjacent long girders of the wing, and a first screw structure is arranged on the outer side of the first end of the base 9, which abuts against the outer side of the long girders, and the position of the base 9 relative to the long girders can be adjusted;

[0055] A stopper 4 is arranged on the outer side of the second end of the base 9, and a first linear guide rail 10 is arranged on the base 9. The stopper 4 is sleeved on the first linear guide rail 10 and connected to the base 9 through a second screw structure. The second rotating handle 8 is used to adjust the second screw structure. By rotating the second rotating handle 8, the stopper 4 is driven to slide on the first linear guide rail 10, thereby adjusting the distance between the stopper 4 and the base 9;

[0056] A support 13 is provided at the first end of the base 9 and below the stopper 4. The support 13 is located below the flange of the long rod. A guide rod is provided on the support 13. A second linear guide rail 12 is provided at the first end of the base 9 and inside the stopper 4. The guide is provided inside the second linear guide rail 12.

[0057] The first end of the base 9 is connected to the support 13, and the stopper 4 is connected to the support 13 through a third screw structure. The third rotating handle 11 is used to adjust the third screw structure. By rotating the third rotating handle 11, the support 13 slides on the second linear guide rail 12, thereby adjusting the distance between the support 13 and the first end of the base 9, and the distance between the support 13 and the stopper 4, so that the base 9 and the support 13 are clamped on the flange of the long stringer;

[0058] The two ends of the stopper 4 are also provided with a fourth rotating screw 5, and the two ends of the fourth rotating screw 5 are also provided with a first rotating handle 6 and a universal support foot 7;

[0059] The universal support foot 7 rests against the aircraft span beam.

[0060] Optionally, threaded holes are provided at both ends of the second rotating circular tube 15, and the first threaded rod 17 and the second threaded rod 18 are threadedly connected in the threaded holes, and the length of the connecting mechanism 2 is adjusted by adjusting the depth of the first threaded rod 17 and the second threaded rod 18 screwed into the threaded holes.

[0061] Optionally, the connecting mechanism 2 further includes: a round tube 16, a connecting piece 19, a rotating handle 20 and a connecting rod 21;

[0062] The round tube 16 is sleeved on the outside of the second rotating round tube 15, and the connecting piece 19 is sleeved on the outside of the round tube 16;

[0063] The second end of the first rotating circular tube 14 is connected to the connecting member 19 through a connecting rod 21. A rotating handle 20 is provided on the connecting member 19. The connecting member 19 is clamped or loosened by rotating the rotating handle 20 to control the sliding of the circular tube 16 on the second rotating circular tube 15, thereby controlling the angle of the connecting rod 21, and further controlling the length and angle of the entire connecting mechanism 2.

[0064] Optionally, a first end of the first rotating circular tube 14 is threadedly connected to a second threaded rod 18 , and the second threaded rod 18 is connected to the base mechanism 1 .

[0065] Optionally, the ring 23 is made of plastic.

[0066] Optionally, one end of the male connector 24 facing the female connector 22 is a φ30 step and an M12 thread.

[0067] The present invention provides a method for fixing an aircraft span beam, comprising the following steps:

[0068] Step 1: Install the aircraft span beam fixing tool on the tooling guide rail and pre-position it by rotating the handle to adjust the top screw on the base top block.

[0069] Step 2: Adjust the telescopic length and angle of the connecting rod of the coupling mechanism so that the female joint at the top of the fixing tool and the male joint on the span beam are at the same height, and lock the coupling mechanism.

[0070] Step 3: Connect the female connector of the aircraft span beam fixing tool to the industrial connector on the aircraft span beam to ensure it is tightened.

[0071] Step 4: Adjust the top screw of the base of the aircraft span beam fixing tool and fix the base on the tooling guide rail to ensure that it cannot move.

[0072] See also Figure 1 The span-wise beam fixing tool comprises 1 base mechanism, 2 connecting mechanisms and 3 joint mechanisms.

[0073] The base mechanism 1 controls the lateral and longitudinal positioning movement of the span-direction beam fixing tool; the connecting mechanism 2 is the main load-bearing part of the span-direction beam fixing tool; and the joint mechanism 3 is used to connect the tool with the product beam.

[0074] See also Figure 2 , by rotating the handle 6 and rotating the screw rod 5, the distance between the stopper 4 and the supporting point of the universal support foot 7 is adjusted; by rotating the handle 8 and rotating the screw rod, the base 9 is adjusted to slide on the linear guide rail 10 to control the distance between the base 9 and the stopper 4.

[0075] See also Figure 3 By rotating the handle 11 and the screw rod, the stopper 4 is adjusted to slide on the linear guide rail 12 to control the distance between the stopper 4 and the support 13.

[0076] See also Figure 4 The first rotating tube 14 and the second rotating tube 15 are rotated to adjust the extension and contraction of the first threaded rod 17 and the second threaded rod 18, so as to change the overall length and angle of the connecting rod. The handle 20 is rotated to clamp or release the connecting piece 19, and the sliding of the tube 16 is controlled, so as to control the angle of the connecting rod 21, and then the length and angle of the entire rod structure are controlled.

[0077] See also Figure 5One end of the female connector 22 is connected to the non-threaded end of the connecting rod 17; one end of the male connector 24 is a φ30 step and an M12 thread, which passes through the φ30 hole at the thin wall of the "I" structure of the product's span beam and is connected to the female connector 22. The material of the ring 23 is plastic, which is placed on both sides of the product to protect the product. The female connector 22 can rotate around the rotating shaft 25 to control the rotation angle of the connector.

Claims

1. An aircraft span beam fixing tool, characterized in that: include: Base mechanism (1), connecting mechanism (2), joint mechanism (3); The connecting mechanism (2) comprises: a first rotating circular tube (14), a second rotating circular tube (15), a first threaded rod (17), and a second threaded rod (18); two ends of the second rotating circular tube (15) are respectively threadedly connected to the first threaded rod (17) and the second threaded rod (18); The joint mechanism (3) comprises: a female joint (22), a ring (23), a male joint (24) and a rotating shaft (25); The base mechanism (1) is arranged on two adjacent long stringers of the wing, the first ends of the first rotating circular tube (14) and the second threaded rod (18) are hinged on the base mechanism (1), and the second end of the first rotating circular tube (14) is slidably connected to the second rotating circular tube (15); One end of the female joint (22) is rotatably connected to the non-threaded end of the connecting rod (17) through a rotating shaft (25); the male joint (24) passes through a hole at the thin wall of the "I"-shaped structure of the span beam and is threadedly connected to the female joint (22), and rings (23) are provided on both sides of the span beam.

2. The aircraft span beam fixing tool according to claim 1, characterized in that: The base mechanism (1) comprises: a stopper (4), a fourth rotating screw (5), a first rotating handle (6), a universal support foot (7), a second rotating handle (8), a base (9), a first linear guide rail (10), a third rotating handle (11), a second linear guide rail (12) and a support (13); The two ends of the base (9) are arranged above two adjacent long girders of the wing, and a first screw structure is arranged on the outer side of the first end of the base (9) and abuts against the outer side of the long girders, so that the position of the base (9) relative to the long girders can be adjusted; A stopper (4) is arranged on the outer side of the second end of the base (9); a first linear guide rail (10) is arranged on the base (9); the stopper (4) is sleeved on the first linear guide rail (10) and connected to the base (9) through a second screw structure; the second rotating handle (8) is used to adjust the second screw structure; by rotating the second rotating handle (8), the stopper (4) is driven to slide on the first linear guide rail (10), thereby adjusting the distance between the stopper (4) and the base (9); A support (13) is provided at the first end of the base (9) and below the stopper (4), the support (13) is located below the flange of the long rod, a guide rod is provided on the support (13), a second linear guide rail (12) is provided at the first end of the base (9) and inside the stopper (4), and the guide is provided inside the second linear guide rail (12); The first end of the base (9) and the support (13), as well as the stopper (4) and the support (13) are connected via a third screw structure. The third rotating handle (11) is used to adjust the third screw structure. By rotating the third rotating handle (11), the support (13) slides on the second linear guide rail (12), thereby adjusting the distance between the support (13) and the first end of the base (9), and between the support (13) and the stopper (4), so that the base (9) and the support (13) are clamped on the flange of the long stringer. A fourth rotating screw (5) is also provided at both ends of the stopper (4), and a first rotating handle (6) and a universal support foot (7) are also provided at both ends of the fourth rotating screw (5); The universal support foot (7) rests against the aircraft span beam.

3. The aircraft span beam fixing tool according to claim 1, characterized in that: Threaded holes are provided at both ends of the second rotating circular tube (15), and the first threaded rod (17) and the second threaded rod (18) are threadedly connected in the threaded holes. The length of the connecting mechanism (2) is adjusted by adjusting the depth of the first threaded rod (17) and the second threaded rod (18) screwed into the threaded holes.

4. The aircraft span beam fixing tool according to claim 1, characterized in that: The connecting mechanism (2) further comprises: a round tube (16), a connecting piece (19), a fourth rotating handle (20) and a connecting rod (21); The circular tube (16) is sleeved on the outside of the second rotating circular tube (15), and the connecting piece (19) is sleeved on the outside of the circular tube (16); The second end of the first rotating circular tube (14) is connected to the connecting member (19) via a connecting rod (21), and a rotating handle (20) is provided on the connecting member (19). By rotating the fourth rotating handle (20) to clamp or release the connecting member (19), the sliding of the circular tube (16) on the second rotating circular tube (15) is controlled, thereby controlling the angle of the connecting rod (21), and further controlling the length and angle of the entire connecting mechanism (2).

5. The aircraft span beam fixing tool according to claim 1, characterized in that: The first end of the first rotating circular tube (14) is threadedly connected to a second threaded rod (18), and the second threaded rod (18) is connected to the base mechanism (1).

6. The aircraft span beam fixing tool according to claim 1, characterized in that: The ring (23) is made of plastic.

7. The aircraft span beam fixing tool according to claim 1, characterized in that: The end of the male connector (24) facing the female connector (22) is a φ30 step and an M12 thread.

8. A method for fixing an aircraft span beam, characterized in that: Using the aircraft span beam fixing tool as described in any one of claims 1 to 7, the aircraft span beam fixing method comprises: The base mechanism (1) is arranged on two adjacent long spars of the wing, and the relative positions of the base (9), the stopper (4) and the support (13) are adjusted by adjusting the first rotating handle (6) and the second rotating handle (8) to perform pre-positioning; Adjusting the telescopic length and angle of the connecting rod of the connecting mechanism (2) so that the height of the female joint (22) and the male joint (24) on the span beam are uniform, and locking the connecting mechanism (2); Connect the female connector (22) to the male connector (24) on the aircraft span beam to ensure tightness; The first rotating handle (6) and the second rotating handle (8) are adjusted to fix the base (9) on the long stringer to ensure that it cannot be moved.

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