Airplane pitot tube off-location auxiliary tool and off-location method

Abstract

The application discloses an off-site auxiliary tool and method for an air speed pipe of an airplane, and the off-site auxiliary tool comprises a clamp body and a protective sleeve, a through hole is formed in the clamp body, the shape of the inner wall of the through hole is consistent with the shape of the surface of the part of the air speed pipe which is in contact with the clamp body, and the clamp body is sleeved on the outside of the air speed pipe through the through hole; and the protective sleeve is sleeved on the abutting surface of the air speed pipe and the clamp body. The application can break the stuck or rusted part of the air speed pipe and the base of the airplane, and the air speed pipe can be conveniently and quickly detached from the airplane, and the air speed pipe can be ensured to be undamaged. The off-site auxiliary tool and method are high in operability, can effectively protect the air speed pipe, save working time, and improve the efficiency of off-site repair.

Description

Technical Field

[0001] This invention relates to the field of aircraft repair technology, specifically to an auxiliary tool and method for removing an aircraft pitot tube. Background Technology

[0002] The pitot tube is an important atmospheric data sensor for aircraft. It uses the pitot tube principle to accurately measure the total atmospheric pressure and static pressure during flight. The data computer then uses formulas such as Bernoulli's total hydrostatic equation to calculate the data such as flight speed, climb rate and atmospheric pressure required for flight control.

[0003] Currently, the common method for repairing aircraft pitot tubes is the off-site repair method. This involves manually rotating the outer wall of the pitot tube to loosen its connection to the aircraft. However, due to harsh operating environments, corrosion, and adhesive residue causing jamming or rust, manual rotation of the pitot tube is often insufficient, making it difficult or impossible to detach it from the aircraft. Furthermore, the surface shape and airflow variations of the pitot tube significantly affect atmospheric parameter collection, requiring strict control over scratches and overall deformation. Consequently, suitable tools are often unavailable, leaving the pitot tube removal process in a passive state, impacting the component disassembly and removal cycle, and resulting in low efficiency for off-site pitot tube repair. Summary of the Invention

[0004] The purpose of this invention is to overcome the above-mentioned technical deficiencies and provide an auxiliary tool and method for removing an aircraft pitot tube, so as to solve the technical problems of difficulty in removing the pitot tube and easy damage during the process of removing the interference fit pitot tube by means of external force in the prior art.

[0005] To achieve the above-mentioned technical objectives, in a first aspect, the present invention provides an auxiliary tool for removing an aircraft pitot tube, comprising a clamp body and a protective sleeve. The clamp body has a through hole formed inside, and the inner wall shape of the through hole matches the shape of the surface of the pitot tube that contacts the clamp body. The clamp body is sleeved on the outside of the pitot tube through the through hole. The protective sleeve is sleeved on the contact surface between the pitot tube and the clamp body.

[0006] Furthermore, the surface of the protective sleeve that contacts the airspeed tube and / or the surface that contacts the clamp body has granular protrusions.

[0007] Furthermore, the displacement auxiliary tool also includes a hollow sleeve, which is sleeved on the outside of the airspeed tube. One end of the hollow sleeve is closed and the other end is open. The open end face of the hollow sleeve abuts against one side end face of the clamp body.

[0008] Furthermore, the clamp body includes a first clamp body and a second clamp body. The first clamp body and the second clamp body are respectively formed with a first locking groove and a second locking groove along the circumferential direction on their outer surfaces. The two first locking grooves and the two second locking grooves are respectively in the same plane.

[0009] Furthermore, the displacement auxiliary tool also includes a locking assembly, which includes a first locking member, a second locking member, and fixing bolts. The first locking member is disposed in two first locking grooves, and the second locking member is disposed in two second locking grooves. The two ends of the first locking member and the second locking member are respectively fastened by fixing bolts.

[0010] Furthermore, the portions of the outer surfaces of the first clamp body and the second clamp body located between the two first locking grooves and the two second locking grooves form a force-bearing portion for binding the belt wrench.

[0011] Furthermore, the clamp body includes a first clamp body and a second clamp body. One end of the first clamp body and the second clamp body are respectively formed with a first insertion portion and a second insertion portion for insertion into the inner cavity of the hollow sleeve. The other end of the first clamp body and the second clamp body are respectively formed with a first blocking portion and a second blocking portion for abutting against the open end of the hollow sleeve.

[0012] Furthermore, the first blocking part and the second blocking part are respectively in the same plane as the end of the hollow sleeve that abuts against it.

[0013] Furthermore, the sides of the first and second blocking parts together form a force-bearing part for binding the belt wrench.

[0014] Secondly, the present invention provides a method for removing an aircraft pitot tube, the method being implemented based on the aircraft pitot tube removal auxiliary tool provided in the first aspect of the present invention, specifically including the following steps:

[0015] A fixture body is manufactured, wherein a through hole is formed inside the fixture body, and the shape of the inner wall of the through hole matches the shape of the surface of the contact part between the airspeed tube and the fixture body.

[0016] The clamp body is fitted onto the part of the airspeed tube that matches the shape of the inner wall of the through hole;

[0017] A protective sleeve is fitted between the clamp body and the airspeed tube;

[0018] The pitot tube can be removed from the aircraft by using a belt wrench to clamp the outside of the clamp body, rotating it and pulling it outward.

[0019] Compared with the prior art, the beneficial effects of the present invention mainly include:

[0020] The pitot tube removal auxiliary tool and method provided by this invention create a force-bearing position on the smooth surface of the pitot tube by sleeved with a clamp body. This allows the pitot tube to be efficiently and quickly removed from the aircraft by using tools such as a belt wrench to clamp the clamp body and pull it outwards while rotating it. Simultaneously, the invention includes a protective sleeve on the contact surface between the clamp body and the pitot tube, protecting the pitot tube during removal, preventing human-caused damage during disassembly, reducing unnecessary losses, and improving removal efficiency and quality. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the pitot tube installation on an aircraft.

[0022] Figure 2 This is a schematic diagram of the overall structure of one embodiment of the present invention;

[0023] Figure 3 yes Figure 2 A partial sectional view;

[0024] Figure 4 This is a schematic diagram of the overall structure of another embodiment of the present invention;

[0025] Figure 5 yes Figure 4 A partial sectional view;

[0026] Figure 6 yes Figure 4 The diagram shows the structure of the first clamp body (the structure of the second clamp body is the same as that of the first clamp body).

[0027] As shown in the figure:

[0028] 1 - Dislocation auxiliary tool, 11 - Clamp body, 111 - First clamp body, 111a - First locking groove, 111b - Second locking groove, 111c - Force receiving part, 111d - First insertion part, 111e - Second insertion part, 111f - First blocking part, 111g - Second blocking part, 12 - Protective sleeve, 13 - Hollow sleeve;

[0029] 2 - Pivot tube;

[0030] 3 - Base;

[0031] 4 - Screws. Detailed Implementation

[0032] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0033] In aircraft repair, the tasks of in-situ and off-site repair of airframe structures and components are plentiful. Various airframe structures and components, due to harsh operating environments, corrosion, and human damage during routine maintenance, face difficulties in off-site removal and may even suffer damage during removal, seriously affecting the completion of repair tasks. The repair of flight atmospheric parameter systems that rely on pitot tube data collection is no exception.

[0034] like Figure 1 As shown, the pitot tube 2 is typically fixed to the aircraft base 3 via an interference fit and auxiliary screws 4. When tightening the screws 4, a thick layer of Y02-2 zinc white paint is applied to the screws 4 to maintain a seal. For removal and repair, the pitot tube 2 is removed from the base 3 by loosening the screws 4 and using external force to overcome the interference fit. However, due to harsh operating environments, corrosion, and adhesive bonding, jamming or rusting often occurs, making it impossible to rotate the pitot tube 2 manually, and no suitable tools are available. Therefore, this invention provides an auxiliary tool and method for removing the aircraft pitot tube.

[0035] Firstly, such as Figures 2-6 As shown, the present invention provides an auxiliary tool 1 for removing an aircraft pitot tube, including a clamp body 11 and a protective sleeve 12. The clamp body 11 is sleeved on the outside of the pitot tube 2, and a through hole is formed inside the clamp body 11. The shape of the inner wall of the through hole matches the shape of the surface of the pitot tube 2 that contacts the clamp body 11. The protective sleeve 12 is sleeved on the contact surface between the pitot tube 2 and the clamp body 11.

[0036] When using the dislocation auxiliary tool 1 provided by this invention to dislocate the airspeed tube 2, the protective sleeve 12 and the clamp body 11 are sequentially placed on the outside of the airspeed tube 2. The clamp body 11 then provides a force-bearing position on the originally smooth outer wall surface of the airspeed tube. At this time, by using tools such as a belt wrench to clamp the clamp body 11 and rotating and pulling it outward, the airspeed tube 2 can be quickly dislocated from the base 3. At the same time, the protective sleeve 12 can protect the airspeed tube 2 during dislocation, avoiding human damage during the disassembly process and reducing unnecessary losses.

[0037] Furthermore, due to harsh operating environments, corrosion, and adhesive bonding, jamming or rusting may occur, potentially preventing the airspeed tube 2 from rotating even when clamping the clamp body 11 with tools such as a belt wrench. In this case, the clamp body 11 can be tapped in the opposite direction of the airspeed tube 2's displacement. The friction of the clamp body 11 will break the jamming part of the airspeed tube 2, after which the clamp body 11 can be clamped again with tools such as a belt wrench. Therefore, the protective sleeve 12 is required to be made of a soft material with a high coefficient of friction, such as rubber.

[0038] Furthermore, in order to increase the friction of the protective sleeve 12, the surface of the protective sleeve 12 that contacts the airspeed tube 2 and / or the surface that contacts the clamp body 11 is formed with granular protrusions. These protrusions help to increase the friction between the protective sleeve 12 and the airspeed tube 2 and between the protective sleeve 12 and the clamp body 11 when the protective sleeve 12 is struck, so that the airspeed tube 2 is loosened on the base 3 and can be quickly removed.

[0039] Furthermore, to increase the striking force applied to the clamp body 11 and facilitate force application, the dislocation auxiliary tool also includes a hollow sleeve 13. The hollow sleeve 13 is fitted over the outside of the airspeed tube 2, with one end closed and the other end open. The open end face of the hollow sleeve 13 abuts against one side end face of the clamp body 11. In use, by striking the closed end of the hollow sleeve 13 with the tool, the open end of the hollow sleeve 13 applies a force to the clamp body 11 in the opposite direction to the dislocation of the airspeed tube 2. Combined with the greater friction of the protective sleeve 12, the airspeed tube 2 can break through the jammed or rusted parts and loosen from the base 3. Then, by using a belt wrench to clamp the clamp body 11, the airspeed tube 2 can be easily dislocated from the base 3.

[0040] Furthermore, such as Figure 2 and Figure 3 As shown, the clamp body 11 includes a first clamp body 111 and a second clamp body (since the second clamp body and the first clamp body 111 have the same structure, only the first clamp body 111 is shown in the figure). The first clamp body 111 and the second clamp body are respectively formed with a first locking groove 111a and a second locking groove 111b along the circumferential direction. The two first locking grooves 111a and the two second locking grooves 111b are respectively in the same plane.

[0041] Furthermore, this embodiment also includes a locking assembly, which includes a first locking member, a second locking member, and fixing bolts. The first locking member is disposed in two first locking grooves 111a, and the second locking member is disposed in two second locking grooves 111b. The two ends of the first locking member and the second locking member are respectively fastened by fixing bolts. That is, the first clamp body 111 and the second clamp body are fixed on the airspeed tube 2 by respectively setting the first locking member and the second locking member in the first locking grooves 111a and the second locking grooves 111b, and locking the first locking member and the second locking member with fixing bolts.

[0042] Furthermore, the portion of the outer side of the first clamp body 111 and the second clamp body located between the two first locking grooves 111a and the two second locking grooves 111b forms a force-receiving portion 111c for binding the belt wrench.

[0043] In the above technical solution, the inner surface of the first clamp body 111 and the second clamp body is a conical surface adapted to the airspeed tube 2. The first clamp body 111 and the second clamp body are combined to form the through hole of the clamp body 11. The first locking member and the second locking member can be used to fix the clamp body 11 firmly at the conical surface where the airspeed tube 2 is connected to the base 3. Then, a belt wrench is used to tie to the force-bearing part 111c of the clamp body 11, and the airspeed tube 2 is rotated and pulled outward. If only a belt wrench is used, it will not work. Rotate the pitot tube 2, then tap the hollow sleeve 13 at the head of the main pitot tube to make the clamp body 11 move the pitot tube 2 towards the base 3, loosening any jammed or rusted parts. During this process, be careful not to tap too much to prevent the pitot tube 2 from contacting the metal step at the connection between the head of the pitot tube 2 and the hollow sleeve 13, or the tail of the pitot tube 2 and the base 3 (within 5mm of movement displacement), which could damage the pitot tube 2. After the pitot tube 2 has moved backward, use a belt wrench or other tools to pull it outward while rotating it to remove the pitot tube 2 from its position.

[0044] Furthermore, such as Figure 4 , 5 As shown in Figure 6, to address the inconvenience of repeatedly disassembling and assembling the first and second locking components in the above technical solution, the first clamp body 111 and the second clamp body are directly fixed using the hollow sleeve 13. Specifically, the clamp body 11 includes a first clamp body 111 and a second clamp body (since the second clamp body and the first clamp body 111 have the same structure, only the first clamp body 111 is shown in the figure). One end of the first clamp body 111 and the second clamp body are respectively formed with a first insertion portion 111d and a second insertion portion 111e for insertion into the inner cavity of the hollow sleeve 13. The other end of the first clamp body 111 and the second clamp body are respectively formed with a first blocking portion 111f and a second blocking portion 111g for abutting against the open end of the hollow sleeve 13.

[0045] In the above technical solution, after the first clamp body 111 and the second clamp body are sleeved on the outside of the airspeed tube 2, they are fixed by inserting the first insertion part 111d and the second insertion part 111e into the inner cavity of the hollow sleeve 13. At the same time, the first blocking part 111f and the second blocking part 111g provide the clamp body 11 with a force-bearing position. When the hollow sleeve 13 is struck, the hollow sleeve 13 pushes the first blocking part 111f and 111g to drive the airspeed tube 2 to move inward. The friction force breaks the jam or rust, thereby dislodging the airspeed tube 2.

[0046] Furthermore, the first blocking part 111f and the second blocking part 111g are respectively in the same plane at the ends that abut against the hollow sleeve 13.

[0047] Furthermore, the sides of the first blocking part 111f and the second blocking part 111g together form a force-receiving part 111c for binding the belt wrench.

[0048] Secondly, the present invention provides a method for removing an aircraft pitot tube, the method being implemented based on the aircraft pitot tube removal auxiliary tool 1 described in the first aspect of the present invention, specifically including the following steps:

[0049] Step 1: Fabricate the fixture body 11. The fixture body 11 has a through hole inside. The shape of the inner wall of the through hole matches the shape of the surface of the airspeed tube 2 that contacts the fixture body 11.

[0050] Step 2: Fit the clamp body 11 onto the part of the surface of the airspeed tube 2 that matches the shape of the inner wall of the through hole;

[0051] Step 3: Install a protective sleeve 12 between the clamp body 11 and the airspeed tube 2;

[0052] Step 4: Use a belt wrench to clamp the outside of the clamp body 11, rotate it and pull it outward to remove the pitot tube 2 from the aircraft base 3.

[0053] Furthermore, both sides of the protective sleeve 12 are provided with granular protrusions.

[0054] In summary, the pitot tube removal auxiliary tool and removal method provided by this invention can break through the jammed or rusted parts between the pitot tube 2 and the aircraft base 3, and easily and quickly remove the pitot tube 2 from the aircraft, while ensuring that the pitot tube 2 is undamaged. It is a highly operable removal auxiliary tool and method that effectively protects the pitot tube 2, saves working time, and improves the efficiency of removal repair.

[0055] The specific embodiments of the present invention described above do not constitute a limitation on the scope of protection of the present invention. Any other corresponding changes and modifications made in accordance with the technical concept of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. An auxiliary tool for removing an aircraft pitot tube, characterized in that, include: The clamp body has a through hole inside, and the shape of the inner wall of the through hole matches the shape of the surface of the contact part between the airspeed tube and the clamp body. The clamp body is sleeved on the outside of the airspeed tube through the through hole. A protective sleeve is fitted onto the contact surface between the airspeed tube and the clamp body. The surface of the protective sleeve that contacts the airspeed tube and / or the surface that contacts the clamp body has granular protrusions. A hollow sleeve is fitted around the outside of the airspeed tube. One end of the hollow sleeve is closed and the other end is open. The open end face of the hollow sleeve abuts against one side end face of the clamp body. The open end of the hollow sleeve can apply a force to the clamp body opposite to the direction of the airspeed tube's displacement, so that the airspeed tube can break through the jammed or rusted parts. The clamp body includes a first clamp body and a second clamp body. One end of the first clamp body and the second clamp body are respectively formed with a first insertion part and a second insertion part for insertion into the inner cavity of the hollow sleeve. The other end of the first clamp body and the second clamp body are respectively formed with a first blocking part and a second blocking part for abutting against the open end of the hollow sleeve. The first blocking part and the second blocking part are respectively in the same plane as the end of the hollow sleeve that abuts against the hollow sleeve. The side surfaces of the first blocking part and the second blocking part together form a force-bearing part for binding the belt wrench.

2. The aircraft pitot tube removal auxiliary tool according to claim 1, characterized in that, The clamp body includes a first clamp body and a second clamp body. The first clamp body and the second clamp body are respectively formed with a first locking groove and a second locking groove along the circumferential direction on their outer surfaces. The two first locking grooves and the two second locking grooves are respectively in the same plane.

3. The aircraft pitot tube removal auxiliary tool according to claim 2, characterized in that, It also includes a locking assembly, which includes a first locking member, a second locking member, and a fixing bolt. The first locking member is disposed in two first locking grooves, and the second locking member is disposed in two second locking grooves. The two ends of the first locking member and the second locking member are respectively fastened by fixing bolts.

4. The aircraft pitot tube repositioning auxiliary tool according to claim 3, characterized in that, The portions of the first clamp body and the second clamp body located between the two first locking grooves and the two second locking grooves form the force-bearing portion for binding the belt wrench.

5. A method for removing an aircraft pitot tube, characterized in that, The removal method is based on the aircraft pitot tube removal auxiliary tool as described in any one of claims 1 to 4, and specifically includes the following steps: A fixture body is manufactured, wherein a through hole is formed inside the fixture body, and the shape of the inner wall of the through hole matches the shape of the surface of the contact part between the airspeed tube and the fixture body. The clamp body is fitted onto the part of the airspeed tube that matches the shape of the inner wall of the through hole; A protective sleeve is fitted between the clamp body and the airspeed tube; The pitot tube can be removed from the aircraft by using a belt wrench to clamp the outside of the clamp body, rotating it and pulling it outward.

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