Pressure measuring device for aerospace craft
By installing a protective cover on the outside of the pressure sensor in aerospace vehicles and using a limiting plate and spring mechanism, the problem of sensor damage has been solved, and the sensor has been protected and can be easily installed and removed.
Patent Information
- Application Number
- CN202520274729.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-02-20
- Publication Date
- 2025-12-30
- Estimated Expiration
- 2035-02-20
AI Technical Summary
The pressure sensors in existing aerospace vehicles lack effective protection and are easily damaged by collisions with foreign objects, affecting the accuracy of pressure measurements.
A protective cover is installed on the outside of the pressure sensor, and the protective cover is detachable and fixed by a limiting plate and a spring mechanism to protect the sensor from collisions with external objects.
It effectively protects the pressure sensor from damage, ensuring accurate pressure measurement and convenient installation and disassembly.
Smart Images
Figure CN223741818U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of aircraft pressure measurement technology, and in particular to a pressure measurement device for aerospace vehicles. Background Technology
[0002] Internal pressure is a crucial parameter for aerospace vehicles during flight. Accurate measurement of internal pressure is essential for safe flight, performance evaluation, and fault diagnosis. Measuring the pressure in areas such as the cockpit, cargo hold, and fuel tanks ensures these components maintain a normal pressure environment during flight. Therefore, pressure measurement devices need high-precision capabilities to accurately capture these pressure changes.
[0003] In the prior art, in order to measure the internal pressure of an aerospace vehicle during flight, a pressure measuring device, namely a pressure sensor, is generally used to measure the pressure. The pressure sensor is installed in multiple pre-prepared locations inside the aerospace vehicle. Although the installed pressure sensor can measure the internal pressure of the aerospace vehicle, there is a lack of corresponding protective measures on the outside of the pressure sensor. When the pressure sensor is hit by a foreign object, it will be damaged, which will affect the pressure sensor's measurement of the internal pressure of the aerospace vehicle. Therefore, a pressure measuring device for aerospace vehicles is proposed. Utility Model Content
[0004] The purpose of this invention is to address the shortcomings of existing technologies where pressure sensors lack adequate external protection, leading to damage when subjected to impacts from external objects, which in turn affects the measurement of internal pressure in aerospace vehicles. Therefore, this invention proposes a pressure measurement device for aerospace vehicles.
[0005] To achieve the above objectives, the present invention adopts the following technical solution:
[0006] A pressure measuring device for an aerospace vehicle includes a connecting plate fixed inside the aerospace vehicle, a pressure sensor for measuring the internal pressure of the aerospace vehicle is provided on one side of the connecting plate, a protective cover is provided on the outside of the pressure sensor, and limiting plates for fixing the protective cover are provided on both sides of the protective cover.
[0007] Preferably, a uniformly distributed mounting groove is provided on one side of the connecting plate, and a uniformly distributed mounting block is fixedly connected to the side of the protective cover near the connecting plate, and the mounting block is slidably connected to the inner wall of the mounting groove.
[0008] Preferably, the pressure sensor is disposed inside the protective cover.
[0009] Preferably, a support plate is symmetrically fixedly connected to the bottom of the protective cover, and the support plate is attached to the bottom of the pressure sensor.
[0010] Preferably, a connecting block is symmetrically fixedly connected to one side of the connecting plate, and a cavity with a rectangular cross-section is provided inside the connecting block. A rectangular opening that communicates with the cavity is opened on the side of the connecting block near the protective cover. Limiting ports are opened on both sides of the protective cover. The limiting plate is slidably connected to the rectangular opening and the limiting port. An inclined surface is provided on one side of the limiting plate.
[0011] Preferably, a rectangular plate is fixedly connected to one side of the limiting plate located inside the cavity, the rectangular plate is slidably connected to the cavity, a spring is fixedly connected to one side of the rectangular plate, one end of the spring is fixedly connected to the inner wall of the cavity, a movable opening communicating with the inside of the cavity is opened at the bottom of the connecting block, a movable plate is fixedly connected to the bottom of the rectangular plate, and the movable plate is slidably connected to the movable opening.
[0012] Compared with the prior art, the beneficial effects of this utility model are as follows:
[0013] When in use, this device can prevent the pressure sensor from being damaged by external objects by setting a protective cover on one side, thus providing effective protection for the pressure sensor. At the same time, the protective cover can be installed, fixed, and removed, making it convenient to install the pressure sensor. Attached Figure Description
[0014] Figure 1 This is a three-dimensional structural diagram of a pressure measuring device for aerospace vehicles proposed in this utility model.
[0015] Figure 2 This is a three-dimensional schematic diagram of the bottom structure of a pressure measuring device for aerospace vehicles proposed in this utility model;
[0016] Figure 3 This is a three-dimensional structural diagram of a pressure measuring device for aerospace vehicles after the protective cover has been removed, as proposed in this utility model.
[0017] Figure 4 This is a schematic diagram of the internal three-dimensional structure of a connecting block in a pressure measuring device for aerospace vehicles proposed in this utility model.
[0018] In the diagram: 1. Connecting plate; 2. Pressure sensor; 3. Protective cover; 4. Limiting plate; 5. Mounting groove; 6. Mounting block; 7. Support plate; 8. Connecting block; 9. Cavity; 10. Rectangular opening; 11. Limiting opening; 12. Inclined surface; 13. Rectangular plate; 14. Spring; 15. Moving opening; 16. Moving plate. Detailed Implementation
[0019] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative effort are within the protection scope of the present utility model.
[0020] Reference Figures 1-4 A pressure measuring device for an aerospace vehicle includes a connecting plate 1 fixed inside the aerospace vehicle, a pressure sensor 2 for measuring the internal pressure of the aerospace vehicle is provided on one side of the connecting plate 1, a protective cover 3 is provided on the outside of the pressure sensor 2, and limiting plates 4 for fixing the protective cover 3 are provided on both sides of the protective cover 3.
[0021] It should be noted that the top of the pressure sensor 2 is generally threaded onto the corresponding equipment, and the bottom of the pressure sensor 2 is connected by a wire. The installation of the pressure sensor 2 is existing technology. The specific model and specifications of the pressure sensor 2 need to be selected and determined according to the actual specifications of the device. The specific selection calculation method adopts existing technology in this field, so it will not be described. Both can be powered by external devices and controlled to turn on and off.
[0022] Furthermore, a uniformly distributed mounting groove 5 is provided on one side of the connecting plate 1, and a uniformly distributed mounting block 6 is fixedly connected to the side of the protective cover 3 near the connecting plate 1. The mounting block 6 is slidably connected to the inner wall of the mounting groove 5. The pressure sensor 2 is located inside the protective cover 3. It should be noted that after the four mounting blocks 6 are inserted into the four mounting grooves 5, the pressure sensor 2 can be initially limited and fixed. At the same time, the rectangular opening will also be aligned with the limiting port 11, making it convenient for the limiting plate 4 to be inserted into the limiting port 11.
[0023] Furthermore, a support plate 7 is symmetrically fixedly connected to the bottom of the protective cover 3. The support plate 7 is attached to the bottom of the pressure sensor 2. It should be noted that the support plate 7 can limit and support the bottom of the pressure sensor 2, preventing the pressure sensor 2 from falling.
[0024] Furthermore, a connecting block 8 is symmetrically fixedly connected to one side of the connecting plate 1. The connecting block 8 has a cavity 9 with a rectangular cross-section inside. A rectangular opening 10 is opened on the side of the connecting block 8 near the protective cover 3, which communicates with the inside of the cavity 9. Limiting openings 11 are opened on both sides of the protective cover 3. The limiting plate 4 is slidably connected to the rectangular opening 10 and the limiting opening 11. An inclined surface 12 is provided on one side of the limiting plate 4. It should be noted that the inclined surface 12 allows the protective cover 3 to squeeze the two limiting plates 4 away from each other. With the spring 14, the limiting plate 4 can be directly inserted into the limiting opening 11, which is more convenient.
[0025] Furthermore, a rectangular plate 13 is fixedly connected to one side of the limiting plate 4 located inside the cavity 9. The rectangular plate 13 is slidably connected to the cavity 9. A spring 14 is fixedly connected to one side of the rectangular plate 13. One end of the spring 14 is fixedly connected to the inner wall of the cavity 9. A movable opening 15 communicating with the inside of the cavity 9 is opened at the bottom of the connecting block 8. A movable plate 16 is fixedly connected to the bottom of the rectangular plate 13. The movable plate 16 is slidably connected to the movable opening 15. It should be noted that the limiting plate 4 can be moved out of the limiting opening 11 by the movable plate 16, so that the protective cover 3 can be taken out, and thus the pressure sensor 2 can be taken out easily.
[0026] Working principle of this utility model:
[0027] First, pressure sensor 2 is installed inside the aerospace vehicle;
[0028] Then, the protective cover 3 is placed on the pressure sensor 2. The protective cover 3 will press the two limiting plates 4 away from each other through the inclined surface 12 and move into the cavity 9. It will also press the spring 14 through the rectangular plate 13 until the four mounting blocks 6 on one side of the protective cover 3 are in contact with the connecting plate 1. Then, the four mounting blocks 6 are controlled to be inserted into the four mounting slots 5 respectively. At this time, the rectangular opening 10 will be aligned with the limiting opening 11. Under the action of the spring 14's restoring force, the limiting plate 4 will be inserted into the limiting opening 11, thus completing the installation and fixing of the protective cover 3.
[0029] Finally, when it is necessary to remove the pressure sensor 2, the limiting plate 4 is moved out of the limiting port 11 by the moving plate 16, and then the protective cover 3 is moved out, so that the pressure sensor 2 can be removed.
[0030] The above are merely preferred embodiments of this utility model, but the scope of protection of this utility model is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in this utility model, based on the technical solution and inventive concept of this utility model, should be included within the scope of protection of this utility model.
Claims
1. Pressure measuring device for aerospace vehicles, comprising a connection plate (1) fixed to the inside of an aerospace vehicle, characterized in that, One side of the connecting plate (1) is provided with a pressure sensor (2) for measuring the internal pressure of the aerospace vehicle, the outer side of the pressure sensor (2) is provided with a protective cover (3), and the two sides of the protective cover (3) are provided with limiting plates (4) for fixing the protective cover (3).
2. A pressure measuring device for an aerospace vehicle as in claim 1, wherein, One side of the connecting plate (1) is provided with a mounting groove (5) in a uniform distribution, and the protective cover (3) is fixedly connected with mounting blocks (6) in a uniform distribution on one side close to the connecting plate (1), and the mounting blocks (6) are in sliding connection with the inner walls of the mounting grooves (5).
3. A pressure measuring device for an aerospace vehicle as recited in claim 1, wherein, The pressure sensor (2) is arranged in the protective cover (3).
4. The pressure measurement device for an aerospace vehicle of claim 1, wherein, The bottom of the protective cover (3) is fixedly connected with a support plate (7) in a symmetrical manner, and the support plate (7) is attached to the bottom of the pressure sensor (2).
5. The pressure measurement device for an aerospace vehicle of claim 1, wherein, One side of the connecting plate (1) is fixedly connected with a connecting block (8) in a symmetrical manner, the connecting block (8) is provided with a cavity (9) with a rectangular cross section in the inside, and the connecting block (8) is provided with a rectangular port (10) penetrating the inside of the cavity (9) on one side close to the protective cover (3), the protective cover (3) is provided with a limiting port (11) on both sides, and the limiting plate (4) is in sliding connection with the rectangular port (10) and the limiting port (11), and one side of the limiting plate (4) is provided with an inclined surface (12).
6. A pressure measuring device for an aerospace vehicle as recited in claim 5, wherein, The limiting plate (4) in the cavity (9) is fixedly connected with a rectangular plate (13) on one side, the rectangular plate (13) is in sliding connection with the cavity (9), a spring (14) is fixedly connected to one side of the rectangular plate (13), one end of the spring (14) is fixedly connected with the inner wall of the cavity (9), a moving port (15) penetrating the inside of the cavity (9) is formed in the bottom of the connecting block (8), a moving plate (16) is fixedly connected to the bottom of the rectangular plate (13), and the moving plate (16) is in sliding connection with the moving port (15).