A tool for removing load-limiting retaining rings on aircraft

Abstract

The present invention discloses a disassembly tool for a load limiting snap ring on an aircraft. A surrounding hole is provided in the middle of the locking base body, a notch is provided on one side surface, and a first threaded hole and a first through hole are provided on the side surface of the notch; the connecting base is fixed under the locking base body and a second threaded hole is provided in the middle; the manual driving seat includes a manual turntable and a first sleeve provided on the manual turntable, a second through hole is provided in the middle, an external thread is provided on the outer wall of the first sleeve, and the first sleeve is threadedly connected to the second threaded hole through the external thread; the lever includes a cylinder and a second sleeve, the second sleeve penetrates into the first sleeve, a third through hole is provided in the middle of the lever, a circular reserved groove is provided at the lower end of the third through hole, and a notch is provided on the side of the cylinder; a screw rod is provided at the distal end of the locking handle, the screw rod is connected to both sides of the notch, and by rotating the screw rod through the locking handle, the surrounding hole can be reduced so that the locking base body tightly holds the valve shaft of the aircraft. The present invention can efficiently disassemble the limiting snap ring under the load force.

Description

Technical Field

[0001] This invention relates to aircraft maintenance tooling technology, specifically to a tooling for removing load-limiting retaining rings on aircraft. Background Technology

[0002] For the valve plate shaft on the bleed air valve of the civil aircraft A320, its extreme position is limited by applying axial pressure through a compression spring, which is kept in a compressed state by a limit snap ring.

[0003] like Figure 11 The diagram shows the structure of the compression spring on the valve shaft of a civil aircraft A320. The compression spring 105 is sleeved on the valve shaft 101. The valve shaft 101 is provided with a fixed ring 106 and a movable ring 104. One end of the compression spring 105 rests on the fixed ring 106, and the other end rests on the movable ring 104. The movable ring 104 can slide on the valve shaft 101. The limiting snap ring 103 is installed in the limiting groove 102 on the valve shaft 101. The movable ring 104 rests on the limiting snap ring 103. At this time, the compression spring 105 is in a compressed state.

[0004] When performing maintenance on the bleed air valves of civil aircraft A320s, it is often necessary to remove the limit circlip. However, because the limit circlip is constantly under the load of the compression spring, removal is quite challenging. The current practice is to use a hand-cranked pressure press to compress the spring and then remove the circlip. This process requires two people, is inefficient, and the compression amount of the hand-cranked pressure press varies depending on the force applied by the operator. Sometimes, excessive force can cause excessive spring compression, damaging the valve's components. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to provide a tooling for removing load-limiting retaining rings on aircraft, which can efficiently disassemble the retaining retaining rings under load.

[0006] To solve the above-mentioned technical problems, the technical solution adopted by the present invention is as follows:

[0007] A tooling for removing load-limiting retaining rings on aircraft, characterized in that it comprises:

[0008] The locking base is cylindrical with a ring hole in the middle and a cut on one side. The cut goes through the top and bottom and also through the ring hole. One side of the cut has a first threaded hole and the other side has a first through hole. The ring hole is used to ring around the valve shaft of the aircraft.

[0009] The connecting base is cylindrical and is fixedly connected to the bottom of the locking base. It has a second threaded hole in the middle, which is used to fit onto the valve plate shaft of the aircraft.

[0010] The manual drive unit includes a manual turntable and a first sleeve mounted on the manual turntable. A second through hole is provided in the middle. In use, it is fitted onto the valve shaft of the aircraft through the second through hole. The outer wall of the first sleeve is provided with external threads. The first sleeve is threaded into the second threaded hole through the external threads.

[0011] The muzzle includes a cylinder and a second sleeve on top of the cylinder. The second sleeve is inserted into the first sleeve. The manual turntable presses down on the cylinder. The muzzle has a third through hole in the middle. In use, the third through hole is fitted onto the valve shaft of the aircraft and fits against the valve shaft. The lower end of the third through hole has a circular pre-reserved groove. There is a gap between the inner wall of the pre-reserved groove and the valve shaft of the aircraft. The side of the cylinder has a notch. During use, the aircraft's limiting spring will be located in the pre-reserved groove, and the aircraft's limiting spring will protrude from the notch. The lower end of the cylinder abuts against the movable ring of the aircraft.

[0012] The locking handle has a screw at its distal end. The screw moves through the first through hole and is threadedly connected to the first threaded hole. The distal end abuts against the outer end of the first through hole. By rotating the screw through the locking handle, the cut can be reduced, thereby reducing the size of the annular hole, so that the locking base is tightly clamped onto the valve plate shaft of the aircraft.

[0013] Optionally, the dismantling fixture also includes a fluoropolymer disc with a fourth perforation in the center and an annular groove below the manual turntable. The fluoropolymer disc is fitted onto the second sleeve and located in the annular groove, with the top of the cylinder resting against the fluoropolymer disc.

[0014] Optionally, the lower end of the reserved groove is provided with a first countersunk hole for fitting onto the movable ring of the aircraft.

[0015] Optionally, the two opposite sides of the cylinder are provided with notches.

[0016] Optionally, the disassembly tooling also includes a positioning pin and a fixing screw. The locking base is provided with a first pin hole and a positioning hole, and the connecting base is provided with a second pin hole and a third threaded hole. The positioning pin passes through the first pin hole and the second pin hole, and the fixing screw passes through the positioning hole and is threaded into the third threaded hole. The fixing screw is used to connect the locking base and the connecting base together.

[0017] Optionally, a groove is provided at the outer end of the corresponding first through hole of the locking base, and the distal end of the locking handle is located in the groove.

[0018] Optionally, a groove is provided on the side wall of the circumferential hole, with the groove and the cut located on opposite sides of the circumferential hole, and the groove penetrating the locking base vertically.

[0019] Optionally, a pattern is provided on the outer surface of the manual turntable to increase friction.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] This invention achieves the locking function through the cooperation of the locking base and the locking handle, which can lock onto the valve shaft of the aircraft, creating a point of force. Then, by rotating the manual turntable, the mullion can be moved to compress the compression spring of the aircraft, so that the compression spring no longer applies pressure to the limiting circlip of the aircraft. The limiting circlip of the aircraft can be easily removed from the notch. It can be seen that the operation of this invention is stable and safe, and the removal of the limiting circlip can be completed by a single person, which is highly efficient.

[0022] This invention applies a stable compression force to the compression spring through a threaded connection structure between the first sleeve and the second threaded hole. The compression amount of the compression spring can be quantitatively adjusted according to the number of rotations of the manual drive seat, which can avoid excessive compression of the compression spring and damage to the components on the valve. Attached Figure Description

[0023] Figure 1 This is a front view schematic diagram of the dismantling tool of the present invention;

[0024] Figure 2 This is a cross-sectional schematic diagram of the dismantling fixture of the present invention;

[0025] Figure 3 This is a cross-sectional schematic diagram of the locking base of the present invention;

[0026] Figure 4 This is a top view of the connecting base of the present invention;

[0027] Figure 5 This is a cross-sectional schematic diagram of the manual drive seat of the present invention;

[0028] Figure 6 This is a top view schematic diagram of the fluoropolymer disc of the present invention;

[0029] Figure 7 This is a cross-sectional schematic diagram of the mullion of the present invention;

[0030] Figure 8 This is a bottom view schematic diagram of the mullion of the present invention;

[0031] Figure 9 This is a top view of the locking handle of the present invention;

[0032] Figure 10 This is a partial cross-sectional view of the dismantling tool of the present invention from a top view perspective;

[0033] Figure 11 This is a schematic diagram of the structure of the compression spring on the valve shaft of a civil aviation A320 aircraft;

[0034] Figure 12This is a schematic diagram illustrating the process of disassembling the limiting circlip of the valve plate on a civil aviation A320 aircraft using the disassembly tooling of the present invention.

[0035] Meaning of the labels in the attached diagram:

[0036] 1-Locking base; 1.1-Groove; 1.2-Positioning hole; 1.3-First pin hole; 1.4-Annular hole; 1.5-First threaded hole; 1.6-Slit; 1.7-First through hole; 1.8-Groove; 2-Connecting base; 2.1-Second threaded hole; 2.2-Third threaded hole; 2.3-Second pin hole; 3-Manual drive seat; 3.1-Manual turntable; 3.2-Pattern; 3.3-First sleeve; 3.4-Annular groove; 3.5-External thread; 3.6-Second 4-Perforation; 4-Fluorine disc; 4.1-Fourth perforation; 5-Mount; 5.1-Cylinder; 5.2-Second sleeve; 5.3-First countersunk hole; 5.4-Pre-reserved groove; 5.5-Third perforation; 5.6-Notch; 6-Positioning pin; 7-Fixing screw; 8-Locking handle; 8.1-Far end of locking handle; 8.2-Screw; 101-Valve disc shaft; 102-Limiting groove; 103-Limiting snap ring; 104-Moving ring; 105-Compression spring; 106-Fixing ring. Detailed Implementation

[0037] The present invention will be further described below with reference to embodiments.

[0038] In the description of this invention, it should be understood that the orientation descriptions, such as up, down, front, back, left, right, etc., are based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting this invention.

[0039] In the description of this invention, "several" means one or more, "more than" means two or more, "greater than," "less than," and "exceeding" are understood to exclude the stated number, while "above," "below," and "within" are understood to include the stated number. The use of "first" and "second" in the description is merely for distinguishing technical features and should not be construed as indicating or implying relative importance, or implicitly indicating the number of indicated technical features, or implicitly indicating the order of the indicated technical features.

[0040] In the description of this invention, unless otherwise explicitly defined, terms such as "set up," "install," and "connect" should be interpreted broadly, and those skilled in the art can reasonably determine the specific meaning of the above terms in this invention in conjunction with the specific content of the technical solution.

[0041] Example:

[0042] like Figure 1 and Figure 2 The image shows a tooling for removing a load-limiting retaining ring on an aircraft according to this embodiment. It includes a locking base 1, a connecting base 2, a manual drive base 3, a mullion 5, a locking handle 8, a fluoropolymer disc 4, a fixing screw 7, and two locating pins 6.

[0043] like Figures 1 to 3 As shown, the locking base 1 is cylindrical with a central circumferential hole 1.4 and a cut 1.6 on one side. The cut 1.6 extends vertically and inwards into the circumferential hole 1.4, giving the locking base 1 an overall C-shape. In this embodiment, a groove 1.8 is provided on the side wall of the circumferential hole 1.4. The groove 1.8 and the cut 1.6 are located on opposite sides of the circumferential hole 1.4. The groove 1.8 extends vertically through the locking base 1, and the groove 1.8 makes the cut 1.6 easier to compress.

[0044] The cut 1.6 has a first threaded hole 1.5 on one side and a first through hole 1.7 on the other side, with the first threaded hole 1.5 and the first through hole 1.7 positioned opposite each other.

[0045] like Figure 9 and Figure 10 As shown, a screw 8.2 is provided at the distal end 8.1 of the locking handle 8. The screw 8.2 is perpendicular to the distal end 8.1 of the locking handle 8. The screw 8.2 moves through the first through hole 1.7 and is threadedly connected to the first threaded hole 1.5. The diameter of the first through hole 1.7 is larger than the diameter of the screw 8.2. The distal end 8.1 of the locking handle 8 abuts against the outer end of the first through hole 1.7.

[0046] In use, the annular hole 1.4 encircles the valve shaft 101 of the aircraft. By rotating the screw 8.2 through the locking handle 8, the distance between the two side walls of the cut 1.6 can be shortened, thus reducing the size of the annular hole 1.4 and tightening the valve shaft 101. This allows the locking base 1 to be tightly secured to the valve shaft 101 of the aircraft, providing a point of force for the compression of the compression spring 105 of the aircraft on the valve shaft 101. The locking structure, in which the locking base 1 and the locking handle 8 cooperate, is simple to operate, stable in use, and improves efficiency.

[0047] Among them, a groove 1.1 is provided at the outer end of the corresponding first through hole 1.7 of the locking base 1, and the far end 8.2 of the locking handle 8 is located in the groove 1.1.

[0048] The connecting base 2, cylindrical in shape, is used to connect the upper and lower parts of the dismantling fixture and is fixedly connected to the bottom of the locking base 1. For example... Figure 4As shown, the middle part of the connecting base 2 is provided with a second threaded hole 2.1. When in use, the second threaded hole 2.1 is used to fit onto the valve plate shaft 101 of the aircraft. A certain distance is set between the inner wall of the second threaded hole 2.1 and the valve plate shaft 101 to accommodate the lower part of the component.

[0049] The fixed connection structure between the connecting base 2 and the locking base 1 is as follows: The locking base 1 has a first pin hole 1.3 and a positioning hole 1.2. There are two first pin holes 1.3, located on opposite sides of the positioning hole 1.2. Correspondingly, the connecting base 2 has a second pin hole 2.3 and a third threaded hole 2.2. There are also two second pin holes 2.3, located on opposite sides of the third threaded hole 2.2. The first pin holes 1.3 and 2.3 are vertically aligned, and the positioning holes 1.2 and 2.2 are vertically aligned. A positioning pin 6 passes through the first pin hole 1.3 and the second pin hole 2.3 to define the position between the connecting base 2 and the locking base 1. A fixing screw 7 passes through the positioning hole 1.2 and is threaded into the third threaded hole 2.2. Tightening the fixing screw 7 connects the locking base 1 and the connecting base 2 together.

[0050] like Figure 5 As shown, the manual drive seat 3 in this embodiment includes a manual turntable 3.1 and a first sleeve 3.3 disposed on the manual turntable. The manual turntable 3.1 and the first sleeve 3.3 are integrally formed. The outer surface of the manual turntable 3.1 is provided with a pattern 3.2 for increasing friction. The manual drive seat 3 has a second through hole 3.6 in the middle, through which it is fitted onto the valve shaft 101 of the aircraft. There is a certain distance between the inner wall of the second through hole 3.6 and the valve shaft 101. The outer wall of the first sleeve 3.3 is provided with an external thread 3.5. The first sleeve 3.3 is threaded into the second threaded hole 2.1 through the external thread 3.5. By rotating the manual turntable 3.1, the position of the manual drive seat 3 can be adjusted up and down.

[0051] In this embodiment, an annular groove 3.4 is provided below the manual turntable 3.1. The annular groove 3.4 is coaxial with the second through hole 3.6. Figure 6 As shown, the fluoropolymer disc 4 has a fourth perforation 4.1 in the middle. The fluoropolymer disc 4.1 is embedded in the annular groove 3.4 and is used for lubrication.

[0052] like Figure 7 and Figure 8As shown, the muzzle 5 includes a cylinder 5.1 and a second sleeve 5.2 disposed on the cylinder 5.1. The cylinder 5.1 and the second sleeve 5.2 are integrally formed. The second sleeve 5.2 passes through the first sleeve 3.3. The muzzle 5 has a third through hole 5.5 in the middle. In use, the third through hole 5.5 is fitted onto the valve shaft 101 of the aircraft and fits against the valve shaft 101. The muzzle 5 can slide along the valve shaft 101. The lower end of the third through hole 5.5 has a circular reserved groove 5.4. The inner wall of the reserved groove 5.4 is spaced from the valve shaft 101 of the aircraft. The reserved groove 5.4 is used to avoid the aircraft's limiting spring 103. The side of the cylinder 5.1 has a notch 5.6. The notch 5.6 is large enough to allow maintenance personnel to remove the aircraft's limiting spring 103 through the notch 5.6 using tools. The lower end of the pre-reserved groove 5.4 is provided with a first countersunk hole 5.3 for fitting onto the movable ring 104 of the aircraft. During use, the upper part of the cylinder 5.1 abuts against the fluoropolymer disc 4. The fluoropolymer disc 4 can reduce the rotational friction between the manual turntable 3.1 and the cylinder 5.1. By rotating and adjusting the manual turntable 3.1, the muzzle 5 can be adjusted downwards. The first countersunk hole 5.3 of the muzzle 5 fits onto the movable ring 104 of the aircraft, so that the lower end of the cylinder 5.1 abuts against the movable ring 104 of the aircraft. The aircraft's limiting circlip 103 will be located in the pre-reserved groove 5.4, and the aircraft's limiting circlip 103 will protrude from the notch 5.6.

[0053] In this embodiment, notches 5.6 are provided on the two opposite sides of the cylinder 5.1.

[0054] The specific usage process of this demolition tool is as follows:

[0055] like Figure 1 and Figure 2 As shown, the locking handle 8 is installed on the locking base 1, and the locking base 1 and the connecting base 2 are fixedly connected together by the positioning pin 6 and the fixing screw 7. The manual drive seat 3 is threaded into the second threaded hole 2.1 of the connecting base 2. The fluoropolymer disc 4 is inserted into the annular groove 3.4 below the manual drive seat 3, and the mullion is installed. Then, as... Figure 12 As shown, the entire dismantling fixture is fitted onto the valve shaft 101. The position is adjusted so that the first countersunk hole 5.3 at the lower end of the muzzle 5 fits onto the aircraft's movable ring 104 and presses against it. The locking handle 8 is rotated, forcing the locking base 1 to contract and deform, reducing the size of the annular hole 4, thereby clamping the valve shaft 101. Then, the manual drive seat 3 is rotated, and the compression spring 105 of the aircraft is compressed through the force of the threaded pair. When the compression reaches a certain amount, the limiting circlip 103 of the aircraft will no longer bear the load force of the compression spring 105. From the notch 5.6, the limiting circlip 103 of the aircraft can be easily removed from the limiting groove 102 using a general tool, such as a hook or screwdriver.

[0056] The above embodiments of the present invention are not intended to limit the scope of protection of the present invention. The implementation of the present invention is not limited thereto. All other modifications, substitutions or alterations made to the above structure of the present invention based on the above content of the present invention, in accordance with ordinary technical knowledge and common practice in the field, without departing from the basic technical idea of ​​the present invention, shall fall within the scope of protection of the present invention.

Claims

1. A tooling for removing load-limiting retaining rings on aircraft, characterized in that, include: The locking base is cylindrical with a circumferential hole in the middle and a cut on one side. The cut extends vertically and inward to the circumferential hole. One side of the cut has a first threaded hole and the other side has a first through hole. The circumferential hole is used to encircle the valve shaft of the aircraft. The connecting base is cylindrical and is fixedly connected to the lower part of the locking base. A second threaded hole is provided in the middle. When in use, the second threaded hole is fitted onto the valve plate shaft of the aircraft. The manual drive unit includes a manual turntable and a first sleeve disposed on the manual turntable. A second through hole is provided in the middle. In use, it is sleeved on the valve shaft of the aircraft through the second through hole. The outer wall of the first sleeve is provided with external threads. The first sleeve is threadedly connected to the second threaded hole through the external threads. The muzzle includes a cylinder and a second sleeve disposed on the cylinder. The second sleeve passes through the first sleeve. The manual turntable is pressed against the cylinder. The muzzle has a third through hole in the middle. In use, the third through hole is fitted onto the valve shaft of the aircraft and fits against the valve shaft. The lower end of the third through hole has a circular pre-reserved groove. There is a gap between the inner wall of the pre-reserved groove and the valve shaft of the aircraft. The side of the cylinder has a notch. During use, the aircraft's limiting spring will be located in the pre-reserved groove, and the aircraft's limiting spring will protrude from the notch. The lower end of the cylinder abuts against the movable ring of the aircraft. The locking handle has a screw at its distal end. The screw moves through the first through hole and is threadedly connected to the first threaded hole. The distal end abuts against the outer end of the first through hole. By rotating the screw through the locking handle, the cut can be reduced, thereby reducing the size of the annular hole, so that the locking base is tightly clamped onto the valve shaft of the aircraft.

2. The fixture for removing the load-limiting retaining ring on an aircraft according to claim 1, characterized in that: The dismantling tool also includes a fluoropolymer disc, which has a fourth through hole in the middle. The manual turntable has an annular groove on its lower side. The fluoropolymer disc is fitted onto the second sleeve and located in the annular groove. The top of the cylinder rests against the fluoropolymer disc.

3. The fixture for removing the load-limiting retaining ring on an aircraft according to claim 1, characterized in that: The lower end of the reserved groove is provided with a first countersunk hole for fitting onto the movable ring of the aircraft.

4. The fixture for removing the load-limiting retaining ring on an aircraft according to claim 1, characterized in that: The cylinder has notches on its two opposite sides.

5. The fixture for removing the load-limiting retaining ring on an aircraft according to claim 1, characterized in that: The dismantling tool also includes a positioning pin and a fixing screw. The locking base is provided with a first pin hole and a positioning hole, and the connecting base is provided with a second pin hole and a third threaded hole. The positioning pin passes through the first pin hole and the second pin hole, and the fixing screw passes through the positioning hole and is threaded into the third threaded hole. The fixing screw is used to connect the locking base and the connecting base together.

6. The fixture for removing the load-limiting retaining ring on an aircraft according to claim 1, characterized in that: A groove is provided at the outer end of the locking base corresponding to the first through hole, and the distal end of the locking handle is located in the groove.

7. The fixture for removing the load-limiting retaining ring on an aircraft according to claim 1, characterized in that: A groove is provided on the side wall of the circumferential hole, and the groove and the cut are located on opposite sides of the circumferential hole. The groove extends through the locking base from top to bottom.

8. The fixture for removing the load-limiting retaining ring on an aircraft according to claim 1, characterized in that: The outer surface of the manual turntable is provided with a pattern to increase friction.

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