Atmospheric data measurement mounting structure

Abstract

The invention provides an atmosphere data measurement and installation structure which comprises a small cylinder assembly, a middle cylinder assembly and a main cylinder assembly which are sequentially connected in the direction from a machine head to a machine tail. The butt joint piece is arranged at the end, away from the main barrel assembly, of the small barrel assembly, a measuring assembly used for measuring atmosphere data is installed at the butt joint piece, and a cable of the measuring assembly is connected with a meteorological measuring device in the machine head through inner cavities of the small barrel assembly, the middle barrel assembly and the main barrel assembly; and the supporting assembly is arranged on a nose of the aircraft, and the middle cylinder assembly and the main cylinder assembly are both connected with the supporting assembly. The invention provides a mounting structure design for additionally mounting the atmosphere data measuring equipment on the aircraft nose, and by adopting the measure, the problem of connection between the atmosphere data measuring equipment and the aircraft body can be solved, and meanwhile, the problem of a channel of an equipment cable can also be solved.

Description

Technical Field

[0001] This invention relates to an installation structure for an atmospheric data measurement device. Background Technology

[0002] With social development and the advancement of science and technology, airplanes have not only become a tool for rapid air transportation but have also gradually become tools capable of performing a variety of special missions. Depending on the different uses of an aircraft, specialized airborne equipment needs to be installed, requiring modification design. Due to the limitations and constraints of the design, production, and use of the selected basic aircraft, as well as the functions, performance, and installation requirements of the airborne equipment, the modification design exhibits different characteristics. Summary of the Invention

[0003] In view of this, the present invention provides an atmospheric data measurement installation structure to solve the problem of installing atmospheric data measurement devices at the nose of the aircraft.

[0004] This invention provides the following technical solution: an atmospheric data measurement installation structure, comprising a small tube assembly, a middle tube assembly, and a main tube assembly, connected sequentially from the nose to the tail; a docking part, disposed at the end of the small tube assembly away from the main tube assembly, wherein a measuring component for atmospheric data measurement is installed at the docking part, and the cable of the measuring component is connected to a meteorological measuring device inside the nose of the aircraft through the inner cavities of the small tube assembly, the middle tube assembly, and the main tube assembly; and a support assembly, disposed on the nose of the aircraft, wherein the middle tube assembly and the main tube assembly are both connected to the support assembly.

[0005] Compared with the prior art, the beneficial effects that can be achieved by the above-mentioned at least one technical solution adopted by the present invention include at least the following: The present invention provides an installation structure design for adding an atmospheric data measurement device to the nose of an aircraft. This measure can solve the connection between the atmospheric data measurement device and the aircraft body, and at the same time solve the channel of the device cable. Attached Figure Description

[0006] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0007] Figure 1 This is a schematic diagram of the overall structure of the present invention; Figure 2 This is a schematic diagram of the front support; Figure 3 This is a schematic diagram of the rear support.

[0008] Explanation of reference numerals in the figure: 11. Connecting part; 12. Small cylinder; 13. External threaded bushing of small cylinder; 14. Internal threaded bushing of middle cylinder; 15. Middle cylinder; 16. External threaded bushing of middle cylinder; 17. Internal threaded bushing of main cylinder; 18. Main cylinder; 19. Flange; 2. Front support; 21. Bearing shell; 22. Base; 3. Rear support; 31. Support bottom surface; 32. Mounting main plate; 33. Reinforcing rib. Detailed Implementation

[0009] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0010] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0011] like Figure 1 and Figure 2 As shown, the atmospheric data measurement installation structure of this embodiment is mainly used for the installation and fixation of atmospheric data measurement equipment at the nose of an aircraft. Its core components include a small cylinder assembly, a middle cylinder assembly, a main cylinder assembly, a docking component 11, and a support assembly. Each component is coaxially connected sequentially along the direction from the nose to the tail, forming a long cantilever support structure. The docking component 11 is used to install the measurement components, and the support assembly ensures a stable connection between the overall structure and the aircraft nose, while also meeting the requirements for the internal arrangement of the measurement component's cables.

[0012] The small cylinder assembly consists of a small cylinder 12 and a small cylinder external threaded bushing 13. The small cylinder 12 is made of 2A12-T4 material, with an outer diameter of 83mm, an inner diameter of 75mm, and a length of 2150mm. The small cylinder external threaded bushing 13 is made of 30CrMnSiA material and is fixedly installed at the end of the small cylinder 12 near the middle cylinder assembly for threaded connection with the middle cylinder assembly. A mating part 11 is fixedly provided at the end of the small cylinder 12 away from the middle cylinder assembly. The mating part 11 is connected to the small cylinder 12 by welding or bolting and is used to support atmospheric data measurement components such as pitot tubes and static pressure holes.

[0013] The intermediate cylinder assembly includes an intermediate cylinder 15, an internal threaded bushing 14, and an external threaded bushing 16. The intermediate cylinder 15 is also made of 2A12-T4 material, with an outer diameter of 110mm, an inner diameter of 100mm, and a length of 2250mm. Both the internal threaded bushing 14 and the external threaded bushing 16 are made of 30CrMnSiA material and are fixed to both ends of the intermediate cylinder 15. The internal threaded bushing 14 is fitted to the external threaded bushing 13 of the smaller cylinder, enabling a threaded connection between the smaller cylinder assembly and the intermediate cylinder assembly; the external threaded bushing 16 is used for connection with the main cylinder assembly. The inner cavity of the intermediate cylinder 15 communicates with the inner cavity of the smaller cylinder 12, providing a channel for the cables of the measuring assembly.

[0014] The main cylinder assembly consists of a main cylinder 18, a main cylinder internal threaded bushing 17, and a flange 19. The main cylinder 18 is made of 2A12-T4 material, with an outer diameter of 134mm, an inner diameter of 120mm, and a length of 2445mm. The main cylinder internal threaded bushing 17 is made of 30CrMnSiA material and is fixed to the end of the main cylinder 18 near the middle cylinder assembly. It is thread-compatible with the middle cylinder external threaded bushing 16, thus connecting the middle cylinder assembly and the main cylinder assembly. The flange 19 is fixed to the end of the main cylinder 18 away from the middle cylinder assembly by bolts. The main cylinder 18 and the flange 19 are connected by 3 rows of M6 bolts arranged axially and 10 evenly distributed in the circumferential direction. The bolt diameter is 6mm to ensure connection strength. The inner cavity of the main cylinder 18 is connected to the inner cavity of the middle cylinder 15. Cables can pass through the inner cavities of the small cylinder assembly, the middle cylinder assembly, and the main cylinder assembly in sequence to achieve electrical connection with the meteorological measuring device inside the machine head.

[0015] The support assembly includes a front support 2 and a rear support 3, both of which are fixed to the side wall of the aircraft nose and are used to support the middle cylinder assembly and the main cylinder assembly. The distance between the two is set to a preferred range of 650mm to 750mm.

[0016] The rear support 3 is a flange docking base, including a support base 31, a mounting plate 32, and reinforcing ribs 33. The support base 31 is inclined to the horizontal direction, conforming to the curved contour of the aircraft nose sidewall, and is fixed to the nose by welding or bolts. The mounting plate 32 is vertically fixed to the support base 31 and has a central through hole and circumferential mounting holes. The central through hole is coaxially connected to the inner cavity of the main cylinder 18, and the circumferential mounting holes are evenly distributed around the central through hole. The flange 19 is bolted to the mounting plate 32 through the circumferential mounting holes, realizing the connection between the main cylinder assembly and the rear support 3, thereby transmitting axial and radial loads. The reinforcing ribs 33 are set between the side of the mounting plate 32 and the support base 31, adopting a triangular support structure to enhance the load-bearing strength of the rear support 3.

[0017] The front support 2 consists of a base 22 and a bearing 21. The bottom surface of the base 22 is inclined to the horizontal direction and fits against the side wall of the machine head. A first semi-circular groove is formed at the upper end. The bearing 21 is fixedly connected to the base 22 by bolts. A second semi-circular groove is formed at the lower end of the bearing 21. The first and second semi-circular grooves cooperate to form a circular receiving part. This receiving part is adapted to the outer diameter of the middle cylinder 15. The middle cylinder assembly is clamped by the bearing, mainly transmitting radial load. Both the base 22 and the bearing 21 are integrally formed with reinforcing ribs to further improve the structural rigidity of the front support 2.

[0018] During assembly, align the external threaded bushing 16 of the middle cylinder with the internal threaded bushing 17 of the main cylinder, and screw it into the main cylinder 18 by rotating the middle cylinder 15; then align the external threaded bushing 13 of the small cylinder with the internal threaded bushing 14 of the middle cylinder, and screw it into the middle cylinder 15 by rotating the small cylinder 12. The main cylinder, middle cylinder, small cylinder and corresponding bushing are further secured by two rows of 6mm diameter bolts along the axial direction to prevent the threaded connection from loosening.

[0019] Due to the threaded connection structure, the screw-in depth of the middle cylinder assembly relative to the main cylinder assembly can be adjusted by rotation, and the screw-in depth of the small cylinder assembly relative to the middle cylinder assembly can be adjusted, thereby achieving the overall cantilever length extension and retraction adjustment to adapt to the installation position requirements of different aircraft models or atmospheric data measurement components. The length ratio of the small cylinder assembly, middle cylinder assembly, and main cylinder assembly is 2150:2250:2445, which simplifies to 430:450:489, corresponding to small cylinder assembly: middle cylinder assembly: main cylinder assembly. This ratio design ensures the stability of the overall structure's center of gravity and reduces the impact of wind resistance and vibration during flight.

[0020] The small cylinder 12, the middle cylinder 15, and the main cylinder 18 are all made of 2A12-T4 aluminum alloy. This material has the characteristics of high strength, light weight, and corrosion resistance. It can reduce the overall weight while ensuring structural strength, which meets the lightweight requirements of airborne equipment. Each threaded bushing is made of 30CrMnSiA alloy structural steel. This material has high hardness, high wear resistance, and good thread processing performance. It can withstand the fastening force of the threaded connection and the friction force during load transmission, avoiding thread wear failure due to long-term use.

[0021] The cables of the atmospheric data measurement component are connected at the docking part 11, pass through the inner cavities of the small cylinder 12, the middle cylinder 15, and the main cylinder 18 in sequence, and enter the head through the central through hole of the rear support 3 to achieve electrical connection with the meteorological measurement device. The built-in cable arrangement can avoid the cables being exposed to the outside and damaged by airflow, rain or foreign objects, while reducing the impact of wind resistance on measurement accuracy and structural stability.

[0022] The above description is merely a specific embodiment of the present invention and should not be construed as limiting the scope of the invention. Therefore, any substitution of equivalent components or equivalent changes and modifications made within the scope of protection of this patent should still fall within the scope of this patent. Furthermore, the technical features, technical features and technical solutions, and technical solutions in this invention can be freely combined and used.

Claims

1. An atmospheric data measurement installation structure, characterized in that, include The small tube assembly, the middle tube assembly, and the main tube assembly are connected sequentially from the head to the tail of the machine. The docking part (11) is located at the end of the small tube assembly away from the main tube assembly. A measuring component for measuring atmospheric data is installed at the docking part (11). The cable of the measuring component is connected to the meteorological measuring device inside the machine head through the inner cavity of the small tube assembly, the middle tube assembly and the main tube assembly. A support assembly is mounted on the nose of the aircraft, and both the middle tube assembly and the main tube assembly are connected to the support assembly.

2. The atmospheric data measurement installation structure according to claim 1, characterized in that, The support assembly includes a rear support (3), which includes: The support base (31) is set on the side wall of the aircraft nose, and the support base (31) is set at an angle to the horizontal direction; The mounting motherboard (32) is set on the support bottom surface (31). The mounting motherboard (32) is provided with a central through hole and a circumferential mounting hole. The central through hole is connected to the inner cavity of the main cylinder assembly. The circumferential mounting holes are evenly distributed along the circumferential interval of the central through hole. The main cylinder assembly is fixedly connected to the rear support (3) through the circumferential mounting holes. A reinforcing rib (33) is provided on the side of the mounting motherboard (32) and connected to the support bottom surface (31).

3. The atmospheric data measurement installation structure according to claim 2, characterized in that, The support assembly includes a front support (2), which includes: The base (22) is set on the side wall of the nose of the aircraft. The bottom surface of the base (22) is inclined to the horizontal direction. The upper end of the base (22) is provided with a first semi-circular groove. The bearing bush (21) is fixedly connected to the base (22). The bearing bush (21) is provided with a second semi-circular groove, and the first semi-circular groove and the second semi-circular groove cooperate to form a receiving part for supporting the middle cylinder assembly.

4. The atmospheric data measurement installation structure according to claim 3, characterized in that, Reinforcing ribs are provided on both the base (22) and the bearing shell (21).

5. The atmospheric data measurement installation structure according to claim 4, characterized in that, The distance between the front support (2) and the rear support (3) is 650mm to 750mm.

6. The atmospheric data measurement installation structure according to claim 1, characterized in that, The length ratio of the small tube assembly, the middle tube assembly, and the main tube assembly is 489:450:

430.

7. The atmospheric data measurement installation structure according to any one of claims 1-4, characterized in that, The small tube assembly, the middle tube assembly, and the main tube assembly all use threaded connections.

8. The atmospheric data measurement installation structure according to any one of claims 1-4, characterized in that, The middle cylinder assembly can extend and retract relative to the main cylinder assembly, and the small cylinder assembly can extend and retract relative to the middle cylinder assembly.

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