Auxiliary tool for removing aircraft reverse thrust fixing bolts

Abstract

The invention discloses an auxiliary tool for removing a reverse thrust fixing bolt of an aircraft, and relates to the technical field of aircraft maintenance tools. The invention comprises the following steps: a fixing sleeve II and a fixing sleeve I are inserted into a groove of a reverse thrust device hanger and connected through a connecting mechanism; a sleeve is inserted into a through hole of the fixing sleeve II; a hexagonal hole of the sleeve is inserted into a hexagonal head of a bolt II; the bolt II is loosened by rotating the sleeve; and a threaded section is then rotated. After the threaded section is rotated, a push column is moved axially. After the push column overcomes the shear force of the bolt II and causes it to move axially, the bolt II can be completely disengaged from the fixing ear, thereby facilitating the removal of the bolt II and improving the removal efficiency and precision of the aircraft engine reverse thrust device.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft maintenance tools, and in particular to an auxiliary tool for removing reverse thrust fixing bolts of an aircraft. Background Art

[0002] The inspection and maintenance of the thrust reverser of an aircraft engine is a routine task during scheduled inspection and maintenance. When performing maintenance work related to the thrust reverser or maintenance work related to the area where the thrust reverser will interfere with the installation, it is usually necessary to remove the thrust reverser. The key point in removing the thrust reverser is to remove the fixing bolts that fix the thrust reverser to the top of the engine. The thrust reverser weighs approximately 300 kg to 800 kg depending on the model. Even if the special tooling for thrust reverser removal is installed and adjusted, the thrust reverser will generate a large shear force on the fixing bolts when in place, making it impossible to remove it by hand or with ordinary wrench tools. Due to the limited space in which it can be operated (as shown in the figure below), it is impossible to use a hammer to knock out the bolts. Therefore, it is very laborious to remove it and it is easy to cause damage to the component structure, increasing the difficulty and workload of the work. Summary of the Invention

[0003] In order to overcome the deficiencies of the above technologies, the present invention provides an auxiliary tooling for fixing bolts that improves the disassembly efficiency of a reverse thrust device of an aircraft engine.

[0004] The technical solution adopted by the present invention to overcome the technical problems is:

[0005] An auxiliary tool for removing aircraft reverse thrust fixing bolts, comprising:

[0006] A fixing sleeve II is disposed in a groove of the reverse thrust device hanger, the fixing sleeve II being located at the left end of the fixing ear in the groove, a through hole being provided in the fixing sleeve II, the axis of the through hole being arranged horizontally in the left-right direction, the inner diameter of the through hole being larger than the outer diameter of the bolt II screwed into the fixing ear, and the through hole and the bolt II being arranged coaxially;

[0007] A fixing sleeve I is arranged in the groove of the reverse thrust device hanger, the fixing sleeve I is located at the right end of the fixing ear in the groove, and a screw hole is provided in the fixing sleeve I, and the axis of the screw hole is arranged horizontally along the left-right direction;

[0008] A top post, the head end of which is coaxially provided with a threaded section, the threaded section being screwed into the screw hole, and the tail end of the top post being in contact with the tail end of the threaded portion of the bolt II;

[0009] A sleeve having a hexagonal hole therein, the hexagonal hole matching the bolt head of the bolt II, and the sleeve being inserted into the through hole of the fixing sleeve II; and

[0010] The connecting mechanism connects and fixes the fixing sleeve I and the fixing sleeve II.

[0011] In order to facilitate the rotation of the top column, it also includes a hexagonal head coaxially arranged at the head end of the threaded section, and the hexagonal wrench is connected to the hexagonal head.

[0012] In order to improve the convenience of use, the above-mentioned hexagonal wrench is a ratchet hexagonal socket wrench.

[0013] In order to improve the convenience of use, a handle is provided at the head end of the sleeve.

[0014] Furthermore, the above-mentioned connecting mechanism includes a connecting plate I arranged on the upper end of the fixing sleeve I and a connecting plate II arranged on the fixing sleeve II. The bolt I passes through the connecting plate I and the connecting plate II in sequence and is locked and fixed by a nut.

[0015] The beneficial effects of the present invention are as follows: the fixing sleeve II and the fixing sleeve I are inserted into the groove of the reverse thrust device hanger and connected through a connecting mechanism, the sleeve is inserted into the through hole of the fixing sleeve II, the hexagonal hole of the sleeve is inserted into the hexagonal head of the bolt II, the bolt II is loosened by rotating the sleeve, and then the threaded section is rotated. After the threaded section rotates, the push column moves axially, and the push column overcomes the shear force of the bolt II so that it moves axially and can be completely disengaged from the fixing ear, so that the bolt II is convenient to remove, and the dismantling efficiency and dismantling accuracy of the aircraft engine reverse thrust device are improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention;

[0017] Figure 2 It is an exploded view of the three-dimensional structure of the present invention;

[0018] In the figure, 1. Thrust reverser hanger 2. Groove 3. Fixing ear 4. Fixing sleeve I 5. Connecting plate I 6. Fixing sleeve II 7. Connecting plate II 8. Bolt I 9. Nut 10. Hexagonal head 11. Hexagonal wrench 12. Socket 13. Handle 14. Hexagonal hole 15. Through hole 16. Bolt II 17. Screw hole 18. Threaded section 19. Jack post. DETAILED DESCRIPTION

[0019] The following is combined with Figure 1 , Attachment Figure 2 The present invention is further described.

[0020] The invention discloses an auxiliary tool for removing the reverse thrust fixing bolts of an aircraft, comprising: a fixing sleeve II 6, which is arranged in the groove 2 of the reverse thrust device hanger 1, the fixing sleeve II 6 is located at the left end of the fixing ear 3 in the groove 2, and a through hole 15 is provided in the fixing sleeve II 6, the axis of the through hole 15 is arranged horizontally in the left-right direction, the inner diameter of the through hole 15 is larger than the outer diameter of the bolt II 16 screwed into the fixing ear 3, and the through hole 15 and the bolt II 16 are arranged coaxially; a fixing sleeve I 4, which is arranged in the groove 2 of the reverse thrust device hanger 1, the fixing sleeve I 4 is located at the right end of the fixing ear 3 in the groove 2, and a screw hole 17 is provided in the fixing sleeve I 4, the axis of the screw hole 17 is arranged horizontally in the left-right direction; a top column 19, a threaded section 18 is coaxially provided at its head end, the threaded section 18 is screwed into the screw hole 17, and the tail end of the top column 19 contacts the tail end of the threaded portion of the bolt II 16; a sleeve 12, a hexagonal hole 14 is provided inside thereof, and the hexagonal hole 14 is in contact with the bolt II The bolt head of the sleeve 16 matches the bolt head of the sleeve 12, which is inserted into the through hole 15 of the fixing sleeve II 6; and a connecting mechanism that connects and secures the fixing sleeve I 4 to the fixing sleeve II 6. When the thrust reverser hanger 1 of the aircraft engine thrust reverser needs to be removed from the aircraft engine, the bolt II 16 needs to be loosened, the fixing sleeve II 6 and the fixing sleeve I 4 are inserted into the groove of the thrust reverser hanger 1 and connected via the connecting mechanism, the sleeve 12 is inserted into the through hole 15 of the fixing sleeve II 6, the hexagonal hole of the sleeve 12 is inserted into the hexagonal head of the bolt II 16, the bolt II 16 is loosened by rotating the sleeve 12, and then the threaded section 18 is rotated. The rotation of the threaded section 18 causes the push post 19 to move axially. The push post 19 overcomes the shear force of the bolt II 16 and causes it to move axially, so that the bolt II 16 can be completely disengaged from the fixing ear 3, facilitating the removal of the bolt II 16 and improving the efficiency and precision of removing the aircraft engine thrust reverser.

[0021] In one embodiment of the present invention, a hexagonal head 10 is coaxially disposed at the end of the threaded segment 18, and a hexagonal wrench 11 is connected to the hexagonal head 10. Inserting the hexagonal wrench 11 into the hexagonal head 10 facilitates rotation of the threaded segment 18, thereby improving operational convenience. Furthermore, the hexagonal wrench 11 is preferably a ratcheting hexagonal socket wrench. The hexagonal wrench 11 facilitates operation in confined spaces, reducing the number of times the wrench 11 needs to be inserted into the hexagonal head 10, further improving operational convenience.

[0022] In one embodiment of the present invention, a handle 13 is provided at the head end of the sleeve 12, and the sleeve 12 can be conveniently driven to rotate by the handle 13, thereby further improving the convenience of operation.

[0023] In one embodiment of the present invention, the connection mechanism includes a connecting plate I 5 disposed on the upper end of the fixing sleeve I 4 and a connecting plate II 7 disposed on the fixing sleeve II 6. Bolts I 8 pass through connecting plate I 5 and connecting plate II 7 in sequence and are then locked and secured by nuts 9. Bolts I 8 and nuts 9 secure connecting plate I 5 to connecting plate II 7, achieving relative locking and fixation of fixing sleeves I 4 and II 6, and providing convenient operation.

[0024] Finally, it should be noted that the above descriptions are merely preferred embodiments of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art will be able to modify the technical solutions described in the aforementioned embodiments or substitute equivalents for some of the technical features. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention.

Claims

1. An auxiliary tool for removing aircraft reverse thrust fixing bolts, characterized in that: include: A fixing sleeve II (6) is arranged in the groove (2) of the reverse thrust device hanger (1), the fixing sleeve II (6) is located at the left end of the fixing ear (3) in the groove (2), a through hole (15) is provided in the fixing sleeve II (6), the axis of the through hole (15) is arranged horizontally along the left and right directions, the inner diameter of the through hole (15) is larger than the outer diameter of the bolt II (16) screwed into the fixing ear (3), and the through hole (15) and the bolt II (16) are arranged coaxially; A fixing sleeve I (4) is arranged in the groove (2) of the reverse thrust device hanger (1), the fixing sleeve I (4) is located at the right end of the fixing ear (3) in the groove (2), and a screw hole (17) is provided in the fixing sleeve I (4), and the axis of the screw hole (17) is arranged horizontally in the left-right direction; A top column (19) is coaxially provided with a threaded section (18) at its head end, the threaded section (18) is screwed into the screw hole (17), and the tail end of the top column (19) contacts the tail end of the threaded portion of the bolt II (16); A sleeve (12) having a hexagonal hole (14) therein, the hexagonal hole (14) matching the bolt head of the bolt II (16), and the sleeve (12) being inserted into the through hole (15) of the fixing sleeve II (6); and A connecting mechanism connects and fixes the fixing sleeve I (4) and the fixing sleeve II (6).

2. The auxiliary tool for removing aircraft reverse thrust fixing bolts according to claim 1, characterized in that: It also includes a hexagonal head (10) coaxially arranged at the head end of the threaded section (18), and a hexagonal wrench (11) is connected to the hexagonal head (10).

3. The auxiliary tool for removing aircraft reverse thrust fixing bolts according to claim 2, characterized in that: The hexagonal wrench (11) is a ratchet hexagonal socket wrench.

4. The auxiliary tool for removing aircraft reverse thrust fixing bolts according to claim 1, characterized in that: A handle (13) is provided at the head end of the sleeve (12).

5. The auxiliary tool for removing aircraft reverse thrust fixing bolts according to claim 1, characterized in that: The connecting mechanism comprises a connecting plate I (5) arranged on the upper end of the fixing sleeve I (4) and a connecting plate II (7) arranged on the fixing sleeve II (6). The bolt I (8) passes through the connecting plate I (5) and the connecting plate II (7) in sequence and is locked and fixed by a nut (9).

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