An eVTOL aircraft airspeed tube mounting structure and eVTOL aircraft

Abstract

The utility model discloses an eVTOL airplane airspeed pipe mounting structure and eVTOL airplane relates to eVTOL airplane technical field, including the body and airspeed pipe, the inner skin and outer skin of body are equipped with coaxial first installation mouth and second installation mouth respectively, the airspeed pipe is worn in first installation mouth with second installation mouth, and airspeed pipe is at least partially located outside outer skin, the inner skin is equipped with mounting seat at first installation mouth, and airspeed pipe is installed on the body through mounting seat. The utility model has the beneficial effect that: through adding mounting seat and airspeed pipe connection on the inner skin of body, make the connecting part of airspeed pipe and body adjust from outer skin to the inner skin, like this, need not set up convex structure on the outer skin, ensure that the outer skin smooth transition, to reduce the aerodynamic resistance of eVTOL airplane.

Description

Technical Field

[0001] This utility model relates to the field of eVTOL aircraft technology, and in particular to an eVTOL aircraft pitot tube mounting structure and an eVTOL aircraft. Background Technology

[0002] On eVTOL aircraft, a pitot tube is usually also installed. The core function of the pitot tube is the same as that of a traditional aircraft: to accurately measure the airspeed (speed relative to the air) and pressure altitude of the aircraft. This is the basic data that is crucial for flight control and safety.

[0003] Currently, pitot tubes are generally installed on the outer skin of eVTOL aircraft. Specifically, a flat surface is protruded from the outer skin to install the pitot tube. However, because this protrusion is convex relative to the outer skin, the outer skin is an uneven surface at this point, which can affect aerodynamics. Utility Model Content

[0004] In view of this, the purpose of this utility model is to provide an eVTOL aircraft pitot tube mounting structure and an eVTOL aircraft to solve the above technical problems.

[0005] This utility model provides an eVTOL aircraft pitot tube mounting structure, including an airframe body and a pitot tube. The inner skin and outer skin of the airframe body are respectively provided with a coaxial first mounting port and a second mounting port. The pitot tube passes through the first mounting port and the second mounting port, and the pitot tube is at least partially located outside the outer skin. The inner skin is provided with a mounting seat at the first mounting port, and the pitot tube is mounted on the airframe body through the mounting seat.

[0006] Optionally, it also includes a cover having a first through hole through which the pitot tube passes, the first through hole being smaller than the size of the second mounting port and aligned with the second mounting port, the cover being disposed on the second mounting port.

[0007] Optionally, the cover includes two cover plates, each cover plate having a matching groove on its edge. When the two cover plates abut against each other sideways, the matching grooves of the two cover plates enclose and form the first perforation.

[0008] Optionally, it also includes a base plate, wherein a second through hole coaxial with the first through hole is provided in the middle of the base plate, the size of the base plate is larger than the size of the second mounting opening, the base plate is installed on the inner surface of the outer skin, and the two cover plates of the cover are detachably installed on the base plate and located in the second mounting opening.

[0009] Optionally, the cross-sectional shape of the cover is consistent with the shape of the second mounting port.

[0010] Optionally, the airspeed tube is detachably connected to the mounting base.

[0011] Optionally, the mounting base includes a mounting plate and a boss on the upper surface of the mounting plate. The mounting plate is mounted on the inner surface of the inner skin, the boss passes through the first mounting opening, and the airspeed tube is connected to the boss.

[0012] Optionally, the top surface of the boss is inclined toward the upper surface of the mounting plate.

[0013] Optionally, the top surface of the boss is provided with a plurality of mounting holes spaced apart, the airspeed tube has a base, and the base of the airspeed tube is provided with assembly holes corresponding to the mounting holes.

[0014] This utility model also provides an eVTOL aircraft, including the eVTOL aircraft pitot tube mounting structure as described above.

[0015] The beneficial effects of this utility model are as follows: by adding a mounting base to the inner skin of the fuselage body to connect with the pitot tube, the connection part between the pitot tube and the fuselage body is adjusted from the outer skin to the inner skin. This eliminates the need to set a protruding structure on the outer skin, ensuring a smooth transition of the outer skin and reducing the aerodynamic drag of the eVTOL aircraft. Attached Figure Description

[0016] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this utility model and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the assembly of the airframe body and the pitot tube in an eVTOL aircraft pitot tube installation structure according to this utility model.

[0018] Figure 2 This is a schematic diagram of the assembly of the outer skin and the pitot tube in an eVTOL aircraft pitot tube mounting structure according to this utility model.

[0019] Figure 3 This is an exploded structural diagram of an eVTOL aircraft pitot tube installation structure according to this utility model.

[0020] Figure 4 This is a schematic diagram of the base plate and the port cover in the eVTOL aircraft pitot tube installation structure of this utility model.

[0021] In the picture: Body 10, inner skin 11, first mounting port 111, outer skin 12, second mounting port 121; Piston tube 20, base 21, mounting hole 211; Mounting base 30, mounting plate 31, fifth through hole 311, boss 32, top surface 321, wire harness through hole 3211; 40, cover plate 41, fourth perforation 411, first perforation 42; Base plate 50, third perforation 51. Detailed Implementation

[0022] The specific embodiments of this utility model will now be described in detail with reference to the accompanying drawings. Obviously, the described embodiments are merely some, not all, of the embodiments of this utility model. Based on the description of this utility model, all other embodiments obtained by those skilled in the art without inventive effort are within the scope of protection of this utility model.

[0023] Unless otherwise explicitly specified and limited, the terms "setup," "installation," and "connection" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium. Those skilled in the art can understand the specific meaning of these terms based on the specific circumstances.

[0024] The terms “upper,” “lower,” “left,” “right,” “front,” “back,” “top,” “bottom,” “inner,” and “outer,” etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product is in use. They are used only for the convenience of description and simplification, 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 limitations on this utility model.

[0025] The terms “first,” “second,” “third,” etc., are used merely to distinguish elements with similar properties, not to indicate or imply relative importance or a specific order.

[0026] The terms “include,” “comprising,” or any other variation thereof are intended to cover non-exclusive inclusion, which includes not only the elements listed but also other elements not expressly listed.

[0027] like Figure 1As shown, this embodiment provides an eVTOL aircraft pitot tube mounting structure, including an airframe 10 and pitot tubes 20. In this embodiment, there are three pitot tubes 20, which are respectively installed on the left and right sides and the bottom of the nose section of the airframe 10. The pitot tubes 20 are used to measure the airspeed and pressure altitude of the aircraft during eVTOL aircraft flight.

[0028] To avoid the protruding portion on the outer skin 12 used to mount the pitot tube 20 in the existing pitot tube mounting structure affecting the aerodynamics of the eVTOL aircraft, such as Figure 2 and Figure 3 As shown in the diagram, in this embodiment, the inner skin 11 and outer skin 12 of the fuselage body 10 are respectively provided with a coaxial first mounting port 111 and a second mounting port 121. Both the first mounting port 111 and the second mounting port 121 are circular holes. The pitot tube 20 passes through the first mounting port 111 and the second mounting port 121, and the pitot tube 20 is at least partially located outside the outer skin 12. The part of the pitot tube 20 outside the outer skin 12 is the functional part of the pitot tube 20 that measures the airspeed and barometric altitude during the flight of the eVTOL aircraft. The inner skin 11 is provided with a mounting base 30 at the first mounting port 111. The mounting base 30 is fixedly connected to the inner skin 11. The pitot tube 20 is connected to the mounting base 30 through its base 21, thereby mounting the pitot tube 20 onto the fuselage body 10.

[0029] The pitot tube mounting structure for eVTOL aircraft provided in this embodiment, compared with the existing pitot tube mounting structure, changes the mounting location of the pitot tube 20 on the fuselage body 10 from the outer skin 12 of the fuselage body 10 to the inner skin 11 of the fuselage body 10. This eliminates the need to form a protruding structure on the outer skin 12 of the fuselage body 10, thereby ensuring the flatness of the outer skin 12 and avoiding the problem of uneven surface of the outer skin 12 caused by the formation of a protruding structure, which would affect the aerodynamics of the eVTOL aircraft.

[0030] Furthermore, in this embodiment, the mounting location of the pitot tube 20 is changed from the outer skin 12 of the fuselage body 10 to the inner skin 11 of the fuselage body 10. To accommodate this mounting method of the pitot tube 20, a second mounting port 121 is provided on the outer skin 12 of the fuselage body 10. Since the cross-sectional dimension of the base 21 of the pitot tube 20 is larger than the cross-sectional dimension of the functional part of the pitot tube 20 (see [link to documentation]), this installation method is suitable for the pitot tube 20. Figure 3The size of the second mounting port 121 must be no smaller than the cross-sectional size of the base 21 of the pitot tube 20 to ensure that the base 21 of the pitot tube 20 can pass through the second mounting port 121 of the outer skin 12 and connect with the mounting seat 30 at the first mounting port 111 on the inner skin 11. However, the cross-sectional size of the functional part of the pitot tube 20 is smaller than the cross-sectional size of the base 21, that is, the cross-sectional size of the functional part of the pitot tube 20 is smaller than the cross-sectional size of the second mounting port 121. This will prevent the outer skin 12 from sealing with the functional part of the pitot tube 20 at the second mounting port 121.

[0031] Therefore, such as Figure 2 and Figure 3 As shown, the eVTOL aircraft pitot tube mounting structure provided in this embodiment also includes a cover 40. The cover 40 has a first through hole 42 through which the functional part of the pitot tube 20 passes. The size of the first through hole 42 is smaller than the size of the second mounting port 121, and the first through hole 42 is aligned with the second mounting port 121. When the pitot tube 20 is connected to the mounting seat 30 on the inner skin 11 via the base 21, the functional part of the pitot tube 20 passes through the first through hole 42 of the cover 40. This allows the cover 40 to seal the gap between the functional part of the pitot tube 20 and the second mounting port 121 of the outer skin 12, ensuring the sealing of the outer skin 12.

[0032] Furthermore, to facilitate the maintenance or replacement of the pitot tube 20, the cover 40 is configured to be detachably mounted on the outer skin 12. However, because the cross-sectional dimension of the base 21 of the pitot tube 20 is larger than the cross-sectional dimension of the functional part of the pitot tube 20, and the first through hole 42 of the cover 40 is to close the gap between the second mounting port 121 of the outer skin 12 and the pitot tube 20, the size of the first through hole 42 is smaller than the cross-sectional dimension of the base 21. The base 21 of the pitot tube 20 cannot pass through the first through hole 42 of the cover 40, and the functional part of the pitot tube 20 is bent, it is impossible to separate the cover 40 and the pitot tube 20 when it is necessary to disassemble or replace the pitot tube 20.

[0033] In this embodiment, the cover 40 is circular and includes two semi-circular cover plates 41. The cover plates 41 are radially recessed along their edges to form matching grooves. After the two cover plates 41 abut against each other with their sides, the matching grooves of the two cover plates 41 enclose and form a first through hole 42. By configuring the circular cover 40 as two separate semi-circular cover plates 41, it can be adapted to the installation of the pitot tube 20. The installation process is as follows: first, the base 21 of the pitot tube 20 and the mounting seat 30 on the inner skin 11 are assembled. At this time, the functional part of the pitot tube 20 passes through the second mounting port 121 of the outer skin 12. Then, the two cover plates 41 enclose the pitot tube 20 from above and below. After the two cover plates 41 are enclosed, the functional part of the pitot tube 20 is located in the first through hole 42 formed by the two matching grooves of the two cover plates 41.

[0034] Furthermore, since the cover 40 is detachably installed with the main body 10, if the connection between the cover 40 and the main body 10 is located on the outer skin 12, the connection between the cover 40 and the outer skin 12 will also cause slight unevenness on the outer skin 12.

[0035] To ensure the flatness of the outer skin 12 at the mounting section of the pitot tube 20 after the cap 40 is connected to the outer skin 12, such as... Figure 4 As shown in the figure, this embodiment also includes a base plate 50, and two cover plates 41 of the cover 40 are mounted on the base plate 50. The center of the base plate 50 has a second through hole (not shown) coaxial with the first through hole 42 of the cover 40. The size of the base plate 50 is larger than the size of the second mounting port 121, so that when the base plate 50 is mounted on the inner surface of the outer skin 12 (the surface facing the cabin), it can cover the second mounting port 121 on the outer skin 12. The size of the second through hole of the base plate 50 is not smaller than the cross-sectional size of the base 21 of the pitot tube 20, ensuring that the base 21 of the pitot tube 20 can pass through the second through hole of the base plate 50. The size of the second through hole is smaller than the size of the second mounting port 121, so that the base plate 50 can be partially aligned with the second mounting port 121. The part of the base plate 50 aligned with the second mounting port 121 can provide mounting positions for the two cover plates 41 of the cover 40. The cover 40 is mounted on the part of the base plate 50 aligned with the second mounting port 121.

[0036] Specifically, the base plate 50 is a circular plate, and a third perforation 51 is formed around its circumference on its surface. Correspondingly, the outer skin 12 has a hole coaxial with the third perforation 51 of the base plate 50. The base plate 50 is installed on the inner surface of the outer skin 12 through the third perforation 51. Since the base plate 50 is located on the inner surface of the outer skin 12, it will not affect the flatness of the outer surface of the outer skin 12. The two cover plates 41 of the cover 40 have a fourth perforation 411 formed around their circumference. Correspondingly, the base plate 50 also has a hole coaxial with the fourth perforation 411. By passing bolts through the fourth perforation 411 on the cover plate 41 and the hole coaxial with the fourth perforation 411 on the base plate 50, and locking them with a support nut, the cover plate 41 can be detachably installed on the base plate 50, and the cover 40 can be detachably installed on the outer skin 12.

[0037] Furthermore, the cross-sectional shape of the cover 40 is consistent with the shape of the second mounting port 121. That is, when the cover 40 is installed on the base plate 50, the cover 40 completely fills the second mounting port 121 of the outer skin 12, further ensuring the flatness of the outer skin 12 at the installation position of the pitot tube 20.

[0038] For the assembly of the pitot tube 20 and the mounting base 30 on the inner skin 11, specifically, the mounting base 30 includes a mounting plate 31 and a boss 32 on the upper surface of the mounting plate 31. The mounting plate 31 is a circular plate, and the mounting plate 31 has a plurality of fifth through holes 311 spaced apart along its circumference. The mounting plate 31 is installed on the inner surface of the inner skin 11 (the surface facing the cabin) through the fifth through holes 311 and bolts. Moreover, the size of the mounting plate 31 is larger than the size of the first mounting opening 111. When the mounting base 30 is installed on the inner surface of the inner skin 11 through the mounting plate 31, the boss 32 passes through the first mounting opening 111, and the base 21 of the pitot tube 20 is connected to the top surface 321 of the boss 32.

[0039] Specifically, the top surface 321 of the boss 32 is provided with multiple mounting holes (not shown in the figure) spaced apart along its circumference. The middle part of the boss 32 is provided with a wire harness through hole 3211, through which the end of the airspeed tube 20 passes and is connected to the wire harness of the body 10. The base 21 of the airspeed tube 20 is provided with an assembly hole 211 corresponding to the mounting hole. The boss 32 is connected to the airspeed tube 20 by bolts passing through the mounting hole and the assembly hole 211 of the base 21 of the airspeed tube 20.

[0040] Furthermore, the top surface 321 of the boss 32 is inclined toward the upper surface of the mounting plate 31 to accommodate the required mounting angle of the airspeed tube 20.

[0041] In summary, the pitot tube mounting structure for eVTOL aircraft provided in this embodiment avoids unevenness on the surface of the outer skin 12, which would otherwise affect eVTOL aerodynamics, by adjusting the connection position between the pitot tube 20 and the fuselage body 10 from the outer skin 12 to the inner skin 11. Furthermore, the second mounting port 121 of the outer skin 12 is sealed by the cover 40, ensuring the airtightness of the outer skin 12. Simultaneously, the cover 40 consists of two separate cover plates 41, which can accommodate the detachable connection between the pitot tube 20 and the mounting base 30.

[0042] This embodiment also provides an eVTOL aircraft, including the eVTOL aircraft pitot tube mounting structure as described above.

[0043] The above description is only a specific embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present utility model should be included within the protection scope of the present utility model.

Claims

1. A pitot tube mounting structure for an eVTOL aircraft, characterized in that: The system includes a body (10) and a pitot tube (20). The inner skin (11) and outer skin (12) of the body (10) are respectively provided with a first mounting port (111) and a second mounting port (121) on the same axis. The pitot tube (20) passes through the first mounting port (111) and the second mounting port (121), and the pitot tube (20) is at least partially located outside the outer skin (12). The inner skin (11) is provided with a mounting seat (30) at the first mounting port (111), and the pitot tube (20) is mounted on the body (10) through the mounting seat (30).

2. The eVTOL aircraft pitot tube mounting structure according to claim 1, characterized in that: It also includes a cap (40) having a first through hole (42) through which the airspeed tube (20) passes. The size of the first through hole (42) is smaller than that of the second mounting port (121), and the first through hole (42) is aligned with the second mounting port (121). The cap (40) is placed over the second mounting port (121).

3. The eVTOL aircraft pitot tube mounting structure according to claim 2, characterized in that: The cover (40) includes two cover plates (41), each cover plate (41) having a matching groove on its edge. When the two cover plates (41) abut against each other on their sides, the matching grooves of the two cover plates (41) enclose and form the first perforation (42).

4. The eVTOL aircraft pitot tube mounting structure according to claim 3, characterized in that: It also includes a base plate (50), in which a second through hole coaxial with the first through hole (42) is opened in the middle. The size of the base plate (50) is larger than the size of the second mounting opening (121). The base plate (50) is installed on the inner surface of the outer skin (12). The two cover plates (41) of the cover (40) are detachably installed on the base plate (50) and located in the second mounting opening (121).

5. The eVTOL aircraft pitot tube mounting structure according to claim 2, characterized in that: The cross-sectional shape of the cover (40) is consistent with the shape of the second mounting port (121).

6. The eVTOL aircraft pitot tube mounting structure according to claim 1, characterized in that: The airspeed tube (20) and the mounting base (30) are detachably connected.

7. The eVTOL aircraft pitot tube mounting structure according to claim 6, characterized in that: The mounting base (30) includes a mounting plate (31) and a boss (32) on the upper surface of the mounting plate (31). The mounting plate (31) is mounted on the inner surface of the inner skin (11). The boss (32) passes through the first mounting port (111). The airspeed tube (20) is connected to the boss (32).

8. The eVTOL aircraft pitot tube mounting structure according to claim 7, characterized in that: The top surface (321) of the boss (32) is inclined toward the upper surface of the mounting plate (31).

9. The eVTOL aircraft pitot tube mounting structure according to claim 8, characterized in that: The top surface (321) of the boss (32) is provided with a plurality of mounting holes spaced apart. The airspeed tube (20) has a base (21), and the base (21) of the airspeed tube (20) is provided with an assembly hole (211) corresponding to the mounting hole.

10. An eVTOL aircraft, characterized in that: Includes the eVTOL aircraft pitot tube mounting structure as described in any one of claims 1-9.

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