Aircraft airspeed tube mounting structure

Abstract

The utility model relates to the field of aviation, in particular to an aircraft airspeed tube mounting structure. The support is used for being fixed to the aircraft inter-wing supporting column and attached to the aircraft inter-wing supporting column, and the inner diameters of the two ends of the installation pipe are adjustable. The installation pipe is used for being connected with an airspeed tube. The support comprises a clamping plate and a supporting pipe allowing a pipeline cable to enter, one side of the clamping plate is tightly screwed to an aircraft inter-wing supporting column, and the other side of the clamping plate is fixedly connected with the supporting pipe. A through hole is formed in the side, close to the clamping plate, of the supporting pipe and used for allowing a full-static-pressure pipeline and a cable to enter the mounting pipe for wiring. One end of the supporting pipe away from the clamping plate is connected with the mounting pipe. According to the utility model, the problem that a fixed-size mounting pipe in a traditional mounting structure cannot adapt to the sizes of struts between wings of different airplanes is solved, and the universality, the adaptability and the mounting and maintenance efficiency of the mounting structure are improved.

Description

Technical Field

[0001] The utility model relates to the field of aviation, in particular to an aircraft pitot tube installation structure. Background Art

[0002] In the aviation field, an aircraft's pitot tube is a key device for measuring aircraft speed. The stability of its installation location and structure is directly related to the accuracy of the measurement data. Traditional aircraft pitot tube installation structures often use fixed-size installation tubes, which have limitations when dealing with different aircraft models or different installation locations. Due to the different shapes and sizes of aircraft interwing struts, fixed-size installation tubes are difficult to adapt to diverse installation requirements, resulting in a complex and time-consuming installation process, and may affect the measurement accuracy of the pitot tube. For example, patent CN215851925U describes a pitot tube installation structure that achieves the closing and fixing of the routing through the cooperation of a movable plate and an extrusion ring, but does not involve the adjustability of the inner diameter of the installation tube, which may limit its adaptability to pitot tubes of different sizes. In addition, patent CN217533261U discloses an eVTOL aircraft pitot tube installation structure. This structure achieves the installation of the pitot tube through a support structure and an adapter structure, but also does not provide a mechanism for adjusting the inner diameter of the installation tube, which may encounter adaptation issues in actual application.

[0003] In traditional installation structures, the connection method between the bracket and the aircraft's wing struts is relatively simple, often requiring customized solutions, which increases manufacturing and maintenance costs. Furthermore, due to the lack of an effective adjustment mechanism, the angle and position of the pitot tube may need to be adjusted to adapt to airflow changes under different flight conditions, but traditional structures make it difficult to achieve fast and precise angle adjustments. Furthermore, regarding the layout of pipes and cables, traditional structures lack adequate protection and are susceptible to external environmental influences such as wear and corrosion. This not only affects aircraft safety but also increases maintenance difficulties.

[0004] In view of the above problems, the present invention aims to design a new aircraft pitot tube installation structure to solve the technical problems in the prior art, improve installation efficiency, ensure measurement accuracy, and enhance the safety and reliability of the aircraft. Utility Model Content

[0005] The utility model aims to provide an aircraft pitot tube installation structure to solve the problems of poor installation adaptability and low installation and maintenance efficiency existing in traditional installation structures.

[0006] To achieve the above objectives, the following technical solutions are adopted.

[0007] An aircraft pitot tube mounting structure, comprising:

[0008] A bracket for fixing on an aircraft's wing strut and fitting the aircraft's wing strut, and a mounting tube with adjustable inner diameters at both ends for connecting to a pitot tube;

[0009] The bracket includes a clamping plate and a support tube for the entry of pipelines and cables. One side of the clamping plate is tightly screwed to the aircraft inter-wing strut, and the other side is fixedly connected to the support tube.

[0010] The support tube is provided with a through hole on one side close to the clamping plate for the full static pressure pipeline and cables to enter the interior of the installation tube for routing;

[0011] One end of the support tube away from the clamping plate is connected to the mounting tube.

[0012] Optionally, the inner diameters of both ends of the mounting tube can be twisted, and the inner twist diameter and length are determined according to the size of the pitot tube, and the pitot tube is connected by fasteners.

[0013] Optionally, a hollow bushing is further installed on the outer periphery of the through hole to protect the full static pressure pipeline and cables from entering the interior of the support tube.

[0014] Optionally, a reinforcement ring for increasing the connection strength is installed on a side of the support tube away from the clamping plate.

[0015] Optionally, the splint includes a mounting portion for installing and fitting on an aircraft wing-to-wing strut, a mounting groove is provided on a side of the mounting portion, the diameter of the mounting groove matches the diameter of the support tube, and one end of the support tube is fixedly connected to the mounting groove.

[0016] Optionally, the support tube is a telescopic tube.

[0017] Optionally, an angle adjustment device is provided at the connection between the clamping plate and the support tube.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] By providing a bracket and a mounting tube with adjustable inner diameters at both ends for connecting to the pitot tube, the problem of the fixed-size mounting tube in the traditional mounting structure being unable to adapt to different aircraft interwing strut sizes is solved, thereby improving the versatility, adaptability, and installation and maintenance efficiency of the mounting structure.

[0020] The adjustable inner diameter design at both ends allows the mounting tube to be adjusted to the specific size of the pitot tube, ensuring a tight fit between the pitot tube and the mounting tube, thereby improving measurement accuracy. This adjustable design also allows for quick installation and replacement of the pitot tube, significantly reducing maintenance time and costs.

[0021] Through the inner diameter twistable design, the inner twist diameter and length can be determined according to the size of the pitot tube, and the pitot tube is connected through the fastener, further improving the flexibility and stability of the installation.

[0022] The hollow bushing mounted on the outer periphery of the through hole effectively protects the total static pressure pipeline and cable, reduces the damage of the external environment to the pipeline and cable, and improves the reliability and durability of the system.

[0023] The reinforcing ring mounted on the side of the support tube away from the clamping plate enhances the connection strength and ensures the stability of the installation structure under various flight conditions.

[0024] The design of the mounting part and the mounting groove on the clamping plate allows the support tube to be fixedly connected in the mounting groove, simplifying the installation process and improving the convenience and accuracy of the installation.

[0025] The design of the support tube as a telescopic tube allows the pipeline to be telescoped as needed, adapting to different installation spaces and improving the flexibility of the installation structure.

[0026] The angle adjusting device provided on the clamping plate allows the angle of the pitot tube to be quickly adjusted according to the flight state, improving the aerodynamic performance of the aircraft and the measurement accuracy. BRIEF DESCRIPTION OF DRAWINGS

[0027] Figure 1 is a structural schematic view of an embodiment of the aircraft pitot tube installation structure of the present application.

[0028] Figure 2 is a structural schematic view of an embodiment of the aircraft pitot tube installation structure of the present application.

[0029] Figure 3 is a structural schematic view of an embodiment of the aircraft pitot tube installation structure of the present application.

[0030] Figure 4 is a structural schematic view of an embodiment of the aircraft pitot tube installation structure of the present application.

[0031] Figure 5 is a structural schematic view of an embodiment of the aircraft pitot tube installation structure of the present application.

[0032] Wherein: 1, support; 11, clamping plate; 12, support tube; 13, through hole; 14, hollow bushing; 15, reinforcing ring; 2, mounting tube; 3, pitot tube. DETAILED DESCRIPTION

[0033] The present application will be described in detail below with reference to the drawings and in combination with the embodiments. It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict.

[0034] The following detailed descriptions are all exemplary descriptions and are intended to provide further details of the present invention. Unless otherwise specified, all technical terms used in this utility model have the same meanings as those commonly understood by those skilled in the art to which this application belongs. The terms used in this utility model are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present utility model.

[0035] Example 1

[0036] like Figures 1-4 As shown, an aircraft pitot tube installation structure is designed to solve the problems in the prior art of poor adaptability of the installation structure, low installation and maintenance efficiency, affected data measurement accuracy, and insufficient protection of pipelines and cables.

[0037] The mounting structure includes a bracket 1, which is constructed and installed as follows: Bracket 1 consists of a clamping plate 11 and a support tube 12. Clamping plate 11 can be designed in an L-shape, with its length and width customized to the dimensions of the aircraft's wing struts to ensure a snug fit. One side of clamping plate 11 is bolted securely to the aircraft's wing struts using standard fasteners, such as screws or bolt sets, to ensure a secure installation.

[0038] The other side of the splint 11 is fixedly connected to the support tube 12 . The diameter of the support tube 12 matches the diameter of the mounting groove on the splint 11 . One end of the support tube 12 is fixedly connected to the mounting groove to form a stable structure.

[0039] Support tube 12 is made of a lightweight, high-strength material, such as aluminum alloy or carbon fiber composite, to reduce the aircraft's weight while maintaining structural strength. On the side near clamping plate 11, support tube 12 is designed with a through-hole 13. The size of through-hole 13 is customized to the dimensions of the full static pressure piping and cables, ensuring smooth routing of these pipes and cables within mounting tube 2.

[0040] The inner diameters of both ends of the mounting tube 2 are adjustable to accommodate pitot tubes 3 of different sizes.

[0041] In order to protect the full static pressure pipeline and cable, a hollow bushing 14 is installed on the outer periphery of the through hole 13. The bushing is made of wear-resistant and corrosion-resistant materials, such as polytetrafluoroethylene (PTFE), to extend the service life and reduce maintenance requirements.

[0042] One end of the support tube 12 away from the clamping plate 11 is connected to the mounting tube 2 and can be connected by welding or bolts to ensure the strength and sealing of the connection and prevent airflow leakage from affecting the measurement accuracy of the pitot tube 3.

[0043] The aircraft pitot tube 3 mounting structure of this utility model can adapt to the interwing struts of different aircraft models, improving installation adaptability and efficiency while ensuring the measurement accuracy of the pitot tube 3 and the safety of the pipelines and cables. This structure is designed with practical operation convenience and ease of maintenance in mind, thereby reducing maintenance costs and improving aircraft safety and reliability.

[0044] Example 2

[0045] The invention relates to an aircraft pitot tube mounting structure. The inner diameters of both ends of the mounting tube 2 can be twisted. The inner twisting diameter and length are determined according to the size of the pitot tube 3. The pitot tube 3 is connected by fasteners.

[0046] The two ends of the mounting tube 2 are designed as a twistable structure, that is, the internal diameters at the two ends of the mounting tube 2 are designed as an adjustable threaded structure. This threaded structure allows adjustment by a manual reamer to adapt to pitot tubes 3 of different sizes.

[0047] Manual reamers come in a variety of sizes. Select the appropriate reamer for the inner diameter of the pitot tube (3) based on the specific dimensions and the required inner diameter of the mounting tube (2). Reamer selection should consider factors such as outer diameter, cutting speed, feed rate, and lead angle to ensure accurate and high-quality apertures.

[0048] Specific steps for inner diameter adjustment:

[0049] First, the outer diameter of the pitot tube 3 is measured to determine the required inner diameter.

[0050] Then, select a suitable reamer. The size of the reamer should be slightly smaller than the outer diameter of the pitot tube 3 to ensure that there is sufficient tightening force between the inner diameter of the mounting tube 2 and the pitot tube 3.

[0051] Use a reamer to twist the inner diameter of the mounting tube 2 until the required inner diameter size and length are reached. In this process, attention should be paid to the selection of cutting fluid for the reamer to reduce the generation of friction and heat and improve processing efficiency and quality.

[0052] Use fasteners, such as bolts or screws, to connect the two ends of the mounting tube 2 with the adjusted inner diameter to the pitot tube 3. The selection of fasteners should take into account the strength of the mounting tube 2 material and the working conditions of the pitot tube 3 to ensure the firmness and reliability of the connection.

[0053] During the connection process, ensure that the torque of the fasteners meets the design requirements to avoid connection problems caused by over-tightening or over-loosening.

[0054] After the inner diameter of the mounting tube 2 is twisted, the pitot tube 3 is inserted into the mounting tube 2 and fixed with fasteners. The inner diameter of the mounting tube 2 should be closely matched with the outer diameter of the pitot tube 3 to ensure that the measurement data of the pitot tube 3 is accurate during the flight of the aircraft.

[0055] The inner diameter of the mounting tube 2 can be designed to be adjustable, which not only improves the adaptability of the mounting structure, but also simplifies the installation process, so that the mounting structure can quickly adapt to different types of air speed tubes 3, and the efficiency of maintenance and replacement is improved.

[0056] The aircraft air speed tube 3 mounting structure can realize quick and accurate inner diameter adjustment, ensure the close fit between the air speed tube 3 and the mounting tube 2, and improve the adaptability and reliability of the aircraft air speed tube 3 installation. The design of this structure considers the convenience of actual operation and the simplicity of maintenance, thereby reducing the maintenance cost and improving the safety and reliability of the aircraft.

[0057] Example 3

[0058] As shown in Figure 2 and Figure 3 , an aircraft air speed tube mounting structure, the outer periphery of the through hole 13 is also provided with a hollow bushing 14 for protecting the pitot tube and cable entering the inside of the support tube 12.

[0059] Specifically, the hollow bushing 14 is designed as a cylindrical structure, and its inner diameter is slightly larger than the outer diameter of the pitot tube and cable, so as to ensure that the tube and cable can pass through smoothly. The material of the bushing is selected to be a high-strength material resistant to wear and corrosion, such as polytetrafluoroethylene (PTFE) or nylon, to provide long-term protection and use.

[0060] The hollow bushing 14 is installed on the outer periphery of the through hole 13 of the support tube 12 near the clamping plate 11. The length of the bushing is determined according to the size of the through hole 13 and the bending radius of the tube and cable, so as to ensure that the tube and cable will not be damaged when entering the inside of the support tube 12.

[0061] The hollow bushing 14 is fixed on the outer periphery of the through hole 13 of the support tube 12 by a clamping groove or a thread. A clamping groove is designed at one end or both ends of the bushing, which matches the corresponding clamping groove on the support tube 12, and is fixed by pressing or rotating. Alternatively, a thread is designed on the outer periphery of the bushing, which matches the internal thread on the support tube 12, and is fixed by rotating and tightening.

[0062] When the pitot tube and cable pass through the hollow bushing 14, the inner surface of the bushing is smooth to reduce friction and ensure that the tube and cable can smoothly enter the inside of the support tube 12. A certain gap is left between the inner diameter of the bushing and the outer diameter of the tube and cable to adapt to different sizes of the tube and cable.

[0063] In order to ensure the sealing of the pitot tube and cable inside the support tube 12, sealing rings or gaskets can be designed at both ends of the hollow bushing 14. These sealing elements can be made of rubber, silicone or other elastic materials to ensure that a good seal is formed between the bushing and the support tube 12, preventing moisture, dust and other impurities from entering.

[0064] The hollow bushing 14 is designed to be easily disassembled and replaced so that when maintaining or replacing the full static pressure pipe and cable, the bushing can be quickly removed for inspection or replacement. The bushing can be disassembled by unfastening the slot or loosening the thread, which is simple and quick to operate.

[0065] The aircraft pitot tube 3 mounting structure of the present invention effectively protects the full static pressure piping and cables, reducing damage to them from the external environment and improving the reliability and durability of the system. Furthermore, the design of the hollow bushing 14 also takes into account the ease of installation and maintenance, reducing maintenance costs and improving the safety and reliability of the aircraft.

[0066] Example 4

[0067] like Figure 5 As shown, an aircraft pitot tube installation structure is provided, in which a reinforcement ring 15 for enhancing the connection strength is installed on the side of the support tube 12 away from the clamping plate 11 .

[0068] The reinforcement ring 15 is an annular structure, and its material is selected from high-strength metal materials, such as stainless steel or aluminum alloy, to ensure that it will not be deformed or damaged when subjected to large stress. The design of the reinforcement ring 15 needs to take into account the material and thickness of the support tube 12 to achieve the best reinforcement effect. The inner diameter of the reinforcement ring 15 is slightly larger than the outer diameter of the support tube 12 to ensure that it can be tightly fitted on the support tube 12. The position of the reinforcement ring 15 is selected on the side of the support tube 12 away from the splint 11, that is, the part where the support tube 12 is connected to the mounting tube 2. This is the area where the support tube 12 is subjected to greater force. The setting of the reinforcement ring 15 can effectively improve the connection strength of this part.

[0069] The reinforcement ring 15 can be secured to the support tube 12 by welding, bolting, or bonding. Welding provides a permanent connection between the reinforcement ring 15 and the support tube 12, while bolting facilitates replacement and maintenance of the reinforcement ring 15. Bonding is suitable for situations where welding is not feasible or where quick installation is required. In such cases, the adhesive selected must possess good temperature and pressure resistance.

[0070] The fit between the reinforcement ring 15 and the support tube 12 must be sufficiently tight to prevent the connection from loosening due to vibration during flight. The outer surface of the reinforcement ring 15 can be designed with ribs or grooves to increase friction with the support tube 12 and improve the stability of the connection.

[0071] The manufacturing process for the reinforcement ring 15 must ensure dimensional accuracy and surface finish. Metal reinforcement rings 15 can be precisely cut and punched using CNC machine tools to ensure a precise fit with the support tube 12. Non-metallic reinforcement rings 15, such as carbon fiber composite rings, can be manufactured using compression molding to achieve both lightweight and high strength.

[0072] The reinforcement ring 15 in the aircraft pitot tube 3 mounting structure of the present invention can effectively improve the strength of the connection between the support tube 12 and the mounting tube 2, reduce the risk of structural damage caused by unstable connection, and thus improve the reliability and safety of the aircraft pitot tube 3 mounting structure.

[0073] Example 5

[0074] A mounting structure for an aircraft pitot tube, wherein a clamping plate 11 includes a mounting portion for mounting and fitting on an aircraft inter-wing strut, a mounting groove is provided on a side of the mounting portion, and the diameter of the mounting groove matches the diameter of a support tube 12, and one end of the support tube 12 is fixedly connected to the mounting groove.

[0075] Specifically, the plate 11 is designed as a flat metal component, its shape and size customized to the specific shape of the aircraft's wing struts to ensure a tight fit. The plate 11 is made of a high-strength aluminum alloy or titanium alloy to ensure stability and durability when subjected to various stresses during flight.

[0076] The mounting portion of the clamping plate 11 is the part that directly contacts the aircraft's wing struts and is designed to match the shape of the wing struts to achieve an optimal fit. The surface of the mounting portion may be treated with special treatments, such as anodizing or sandblasting, to increase friction and corrosion resistance.

[0077] The side of the mounting portion is provided with a mounting groove, the diameter of which is slightly larger than the outer diameter of the support tube 12 to ensure that the support tube 12 can be smoothly inserted. The manufacturing of the mounting groove can be precisely processed by CNC machine tools to ensure dimensional accuracy and surface finish.

[0078] One end of the support tube 12 is designed to be fixedly connected to the mounting groove, and this fixed connection can be achieved by welding, threading or snapping, etc. The material of the support tube 12 is also selected to be a high-strength metal or composite material to ensure that it can withstand various stresses during flight.

[0079] The specific method of fixing one end of the support tube 12 in the installation groove can be: a thread is designed on the outer periphery of the support tube 12, which matches the internal thread in the installation groove, and fixation is achieved by rotating and tightening; or a card slot is designed at the end of the support tube 12, which matches the buckle in the installation groove, and fixation is achieved by locking the buckle.

[0080] During the installation process, first fit the mounting portion of the splint 11 onto the aircraft wing support, then insert one end of the support tube 12 into the mounting groove, and adjust the position of the support tube 12 as needed, and finally fix the support tube 12 in the mounting groove using the above-mentioned fixing method.

[0081] The aircraft pitot tube 3 mounting structure of the present invention can ensure that the clamping plate 11 fits tightly against the aircraft inter-wing strut, while the fixed connection between the support tube 12 and the clamping plate 11 is stable and reliable, thereby improving the stability of the mounting structure and the safety of the aircraft.

[0082] Example 6

[0083] An aircraft pitot tube installation structure, wherein the support tube 12 is a telescopic tube.

[0084] Specifically, support tube 12 is designed as a telescopic tube, consisting of a fixed tube and a slidable telescopic portion. This allows the length of support tube 12 to be adjusted to accommodate different installation requirements for pitot tube 3. The entire telescopic tube is constructed from a lightweight, high-strength metal or alloy, such as aluminum alloy or stainless steel, to ensure stability and durability under various stresses experienced during flight.

[0085] The telescopic tube consists of a fixed tube and a telescopic rod that can slide within the fixed tube. A first, inward-facing stop flange is provided at one end of the fixed tube, while a second stop flange is also provided within the fixed tube. A third, outward-facing stop flange is provided at one end of the telescopic rod. The telescopic rod is inserted into the fixed tube and can reciprocate along the axis of the fixed tube.

[0086] The telescopic tube works by allowing an external force to push the extension rod past the second stop boss. When the extension rod reaches its maximum limit, the third stop boss engages between the first and second stop bosses. To retract the extension tube, external force is applied to push the extension rod into the fixed tube, causing the third stop boss to pass over the second stop boss, allowing the entire tube to retract into the fixed tube.

[0087] In order to maintain the sealing between the telescopic tube and the fixed tube, a sealing ring is sleeved on the telescopic tube. When the telescopic rod moves to the longest limit position, the sealing ring is stuck between the first limit boss and the third limit boss.

[0088] One end of the fixed tube of the telescopic tube is fixedly connected to the mounting groove of the clamping plate 11, and the other end is connected to the telescopic rod via a limit boss and a sealing ring. During installation, the length of the support tube 12 can be adjusted by rotating or pushing and pulling the telescopic rod to ensure the correct installation and alignment of the pitot tube 3.

[0089] The telescopic tube in the aircraft pitot tube 3 mounting structure of the present invention can be adjusted in length to accommodate different aircraft models and different mounting locations, thereby improving the flexibility and adaptability of the mounting structure while also ensuring the accuracy of the pitot tube 3 installation and the aerodynamic performance of the aircraft.

[0090] Example 7

[0091] An aircraft pitot tube mounting structure is provided, wherein an angle adjustment device is provided at the connection between a clamping plate 11 and a support tube 12.

[0092] Specifically, the angle adjustment device is intended to provide a mechanism capable of adjusting the angle of the support tube 12 relative to the clamping plate 11, so as to adjust the angle of the support tube 12 during installation or according to actual flight conditions to ensure the correct positioning of the pitot tube 3 and optimal airflow contact.

[0093] The angle adjustment device includes a rotating base provided on the clamping plate 11 and an adjustment arm connected to the support tube 12. The rotating base is fixed to the upper surface of the clamping plate 11, and one end of the adjustment arm is hinged on the rotating base and the other end is connected to the support tube 12.

[0094] The rotating base is designed as a circular plate with a central shaft. The central shaft is equipped with threads to mate with the matching threads on the adjustment arm. By rotating the central shaft, the adjustment arm connected to the central shaft can be rotated around the hinge point to achieve angle adjustment.

[0095] The adjusting arm is a rotatable arm-shaped structure, one end of which is connected to the central axis on the rotating base through a threaded connection, and the other end is connected to the support tube 12. The design of the adjusting arm allows it to rotate on the rotating base to adjust the angle of the support tube 12.

[0096] By rotating the central axis of the rotating base manually or with a power tool, the adjusting arm rotates accordingly, thereby driving the support tube 12 to rotate around the clamping plate 11 to adjust the angle. During the rotation process, the angle of the support tube 12 can be accurately controlled and displayed by a scale indicator or angle sensor set on the rotating base.

[0097] In order to fix the adjusted angle, a locking mechanism, such as a locking nut or a locking pin, is provided on the rotating base for locking the central axis after adjusting to the desired angle to prevent accidental rotation of the rotating arm during flight.

[0098] All components of the angle adjustment device are made of high-strength, corrosion-resistant materials such as stainless steel or aluminum alloy to ensure reliability and durability under various flight conditions.

[0099] The angle adjustment device in the aircraft pitot tube 3 mounting structure of the present invention can achieve rapid and precise angle adjustment, ensuring that the angle of the connection between the support tube 12 and the clamping plate 11 can be adjusted as needed to adapt to different installation and flight conditions, thereby improving the flexibility and accuracy of the aircraft pitot tube 3 installation.

[0100] It is understood from common technical knowledge that the present invention may be implemented through other embodiments that do not depart from its spirit or essential features. Therefore, the embodiments disclosed above are, in all respects, merely illustrative and not exclusive. All modifications within the scope of the present invention or equivalent to the scope of the present invention are intended to be encompassed by the present invention.

Claims

1. An aircraft pitot tube installation structure, characterized in that: include: A bracket (1) for fixing on an aircraft wing strut and fitting the aircraft wing strut, and a mounting tube (2) with adjustable inner diameters at both ends for connecting to a pitot tube (3); The bracket (1) comprises a clamping plate (11) and a support tube (12) for the entry of pipelines and cables; one side of the clamping plate (11) is tightly screwed onto the aircraft wing strut, and the other side is fixedly connected to the support tube (12); The support tube (12) is provided with a through hole (13) on one side close to the clamping plate (11), for allowing the full static pressure pipeline and cables to enter the interior of the installation tube (2); One end of the support tube (12) away from the clamping plate (11) is connected to the mounting tube (2).

2. The aircraft pitot tube mounting structure according to claim 1, characterized in that: The inner diameters of both ends of the installation tube (2) can be twisted, and the inner twist diameter and length are determined according to the size of the pitot tube (3), and the pitot tube (3) is connected via fasteners.

3. The aircraft pitot tube mounting structure according to claim 1, characterized in that: A hollow bushing (14) is also installed on the outer periphery of the through hole (13) for protecting the full static pressure pipeline and cables from entering the inner wiring of the support tube (12).

4. The aircraft pitot tube mounting structure according to claim 1, characterized in that: A reinforcement ring (15) for enhancing connection strength is installed on the side of the support tube (12) away from the clamping plate (11).

5. The aircraft pitot tube mounting structure according to claim 1, characterized in that: The splint (11) includes a mounting portion for mounting and fitting on an aircraft wing strut, a mounting groove is provided on a side surface of the mounting portion, the diameter of the mounting groove matches the diameter of the support tube (12), and one end of the support tube (12) is fixedly connected to the mounting groove.

6. The aircraft pitot tube mounting structure according to claim 1, characterized in that: The support tube (12) is a telescopic tube that can be telescoped along its own axial direction.

7. The aircraft pitot tube mounting structure according to claim 1, characterized in that: An angle adjustment device for adjusting the angle of the support tube (12) is provided at the connection between the clamping plate (11) and the support tube (12).

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