Separated static pressure probe and aircraft
By designing an airflow shielding structure on the static pressure acquisition probe and adjusting the airflow state, the problem of interference with data caused by installation position and attitude was solved, thereby improving the stability and accuracy of static pressure acquisition data, which is suitable for electric vertical take-off and landing aircraft.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- SHANGHAI TCAB TECHNOLOGY CO LTD
- Filing Date
- 2025-07-16
- Publication Date
- 2026-05-15
AI Technical Summary
The data stability and accuracy of existing split-type static pressure acquisition probes are greatly affected by the installation location and the attitude of the aircraft, resulting in unstable and inaccurate data acquisition.
A separate static pressure probe is designed, which uses an airflow shielding structure protruding from the outer side of the acquisition end face to adjust the airflow state near the static pressure acquisition hole and reduce the interference of installation position and aircraft attitude on the data.
It improves the stability and accuracy of static pressure data acquisition, reduces the need for data correction, and enables accurate airspeed measurement at different flight angles of attack.
Smart Images
Figure CN224247062U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of aircraft technology, and in particular to a detachable static pressure probe and an aircraft. Background Technology
[0002] With the gradual development of the low-altitude economy, various types of electric vertical takeoff and landing (eVTOL) aircraft are being rapidly developed. Accurate altitude and airspeed are crucial for eVTOL flight. These two parameters typically require precise hydrostatic data, usually acquired using a separate hydrostatic acquisition probe. However, the data acquired by this separate probe is significantly affected by its installation location (on the aircraft) and the aircraft's attitude (e.g., angle of attack), resulting in poor stability and accuracy of the acquired data. Utility Model Content
[0003] Therefore, it is necessary to provide a separate static pressure probe that can reduce the interference of installation position and aircraft attitude on the acquired data, so as to improve the stability and accuracy of the acquired data.
[0004] This utility model provides a split static pressure probe, comprising:
[0005] The main structure has a collection end face, on which a static pressure collection hole is formed; and
[0006] An airflow blocking structure protrudes from the collection end face and is located outside the static pressure collection hole to block the airflow from the static pressure collection hole.
[0007] In one embodiment, there are multiple static pressure sampling holes, which are arranged at intervals; and / or
[0008] The height of the airflow shielding structure is 2-10mm in the direction perpendicular to the collection end face.
[0009] In one embodiment, the airflow blocking structure is a closed annular structure or an annular structure with a gap.
[0010] In one embodiment, the airflow blocking structure is a ring-shaped structure with a notch, and the notch angle of the airflow blocking structure is greater than 0° and less than or equal to 180°; and / or
[0011] The main structure is cylindrical, and the annular structure is a circular ring structure. The outer periphery of the end face of the annular structure near the acquisition end face coincides with the outer periphery of the acquisition end face.
[0012] In one embodiment, the outer surface of the airflow shielding structure has a slope, which is inclined toward the static pressure collection hole and forms an acute angle with the collection end face.
[0013] In one embodiment, the acute angle is greater than or equal to 30°.
[0014] In one embodiment, the main structure further includes a static pressure output terminal, which is located at the end of the main structure away from the acquisition end face, for outputting the acquired static pressure; and / or
[0015] The split static pressure probe also includes a mounting structure, which is located on the main structure.
[0016] In one embodiment, there are five static pressure sampling holes, which are arranged at intervals in a cross shape; and / or
[0017] The notch angle of the airflow shielding structure is 90°; and / or
[0018] The separate static pressure probe also includes a mounting structure, which is a closed-loop structure. The mounting structure is sleeved on the circumference of the main structure and has multiple mounting through holes arranged at intervals along the circumference.
[0019] This utility model also provides an aircraft, comprising:
[0020] The aircraft itself; and
[0021] In the aforementioned split static pressure probe, the main structure is located on the aircraft body, and at least a portion of the airflow shielding structure protrudes from the outer surface of the aircraft body and is located on the windward side of the split static pressure probe.
[0022] In one embodiment, the airflow shielding structure is entirely exposed from the outer surface of the aircraft body; and / or
[0023] The airflow shielding structure exposed on the outer surface of the aircraft body has a dimension smaller than the boundary layer; and / or
[0024] The main structure is located on the side of the fuselage of the aircraft body; and / or
[0025] When the airflow blocking structure is a ring-shaped structure with a notch, a surface perpendicular to the airflow direction divides the airflow blocking structure into a first half-ring and a second half-ring. The first half-ring is located on the windward side of the split static pressure probe, and the second half-ring is located on the leeward side of the split static pressure probe. The notch is located on the second half-ring; and / or
[0026] The aircraft body is the body of an electric vertical takeoff and landing aircraft.
[0027] When using the above-mentioned split static pressure probe, at least part of the airflow shielding structure can be located on the windward side of the split static pressure probe. Thus, when the airflow flows towards the split static pressure probe, the airflow shielding structure, which protrudes from the acquisition end face and is located outside the static pressure acquisition hole, can be located on the flow path of the airflow and shield the airflow for the static pressure acquisition hole. This allows for targeted adjustment of the airflow state near the static pressure acquisition hole, thereby changing the local airflow state near the static pressure acquisition hole and consequently changing the static pressure acquired by the static pressure acquisition hole.
[0028] When the aforementioned split static pressure probe is applied to an aircraft, the airflow shielding structure alters the local airflow state near the static pressure sampling port, allowing locations that previously did not meet installation requirements (areas with poor airflow stability) to now meet those requirements, thus reducing the demands on the installation location. Furthermore, according to the attached... Figure 6 It is known that when the static pressure acquisition probes are installed in the same position (both installed on the side of the aircraft fuselage), the dimensionless static pressure data collected by traditional static pressure acquisition probes (without airflow obstruction structure and whose acquisition end face does not protrude from the outer surface of the aircraft body) will change significantly under different flight angles of attack. This data change will make the airspeed measurement of the aircraft inaccurate. However, the aforementioned static pressure acquisition probe (with at least part of the airflow obstruction structure exposed from the outer surface of the aircraft body and located on the windward side of the split static pressure probe) can make the slope of the collected dimensionless static pressure data very flat (with very small change) because the airflow obstruction structure can change the local airflow state near the static pressure acquisition hole. This allows the data provided to accurately measure the airspeed of the aircraft at different flight angles of attack. Moreover, the aforementioned static pressure acquisition probe can change the average value of the collected dimensionless static pressure data, that is, it can reduce the average deviation of the originally collected data, so that the measurement data can be used directly without data correction. Therefore, the aforementioned split static pressure acquisition probe can reduce the interference of installation location and aircraft attitude on the acquired data, thereby improving the stability and accuracy of the acquired data. Attached Figure Description
[0029] Various other advantages and benefits will become apparent to those skilled in the art upon reading the detailed description of the preferred embodiments below. The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of this application. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings:
[0030] Figure 1 This is a three-dimensional structural diagram of a split static pressure probe according to an embodiment of the present invention;
[0031] Figure 2 for Figure 1A top view of the split hydrostatic probe shown;
[0032] Figure 3 for Figure 1 The side view of the split hydrostatic probe shown;
[0033] Figure 4 for Figure 1 The side view (with parameters) of the split hydrostatic probe is shown.
[0034] Figure 5 for Figure 1 A top view (with parameters) of the split hydrostatic probe shown;
[0035] Figure 6 The diagram shows the test results of the present invention's detachable static pressure probe and the traditional detachable static pressure probe applied to an aircraft. Detailed Implementation
[0036] To make the above-mentioned objectives, features, and advantages of this application more apparent and understandable, the specific embodiments of this application are described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a thorough understanding of this application. However, this application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of this application. Therefore, this application is not limited to the specific embodiments disclosed below.
[0037] In the description of this application, it should be understood that, where they appear, the terms “center,” “longitudinal,” “lateral,” “length,” “width,” “thickness,” “upper,” “lower,” “front,” “rear,” “left,” “right,” “vertical,” “horizontal,” “top,” “bottom,” “inner,” “outer,” “clockwise,” “counterclockwise,” “axial,” “radial,” and “circumferential” indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this application and simplifying the description, 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 application.
[0038] Furthermore, where applicable, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.
[0039] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," "fixing," etc., shall be interpreted broadly. For example, they may refer to a fixed connection, a detachable connection, or an integral part; they may refer to a mechanical connection or an electrical connection; they may refer to a direct connection or an indirect connection through an intermediate medium; they may refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.
[0040] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.
[0041] It should be noted that, if an element is described as "fixed to" or "set on" another element, it can be directly on the other element or there may be an intervening element. When an element is described as "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementation.
[0042] like Figures 1-5 As shown, a split static pressure probe 10 according to an embodiment of the present invention is presented. The split static pressure probe 10 includes a main body structure 200 and an airflow blocking structure 300. The main body structure 200 has a collection end face 210. A static pressure collection hole 212 is formed on the collection end face 210. The airflow blocking structure 300 protrudes from the collection end face 210 and is located outside the static pressure collection hole 212 to block the airflow from the static pressure collection hole 212.
[0043] When using the aforementioned split static pressure probe 10, at least a portion of the airflow shielding structure 300 can be located on the windward side of the split static pressure probe 10. Thus, when the airflow flows toward the split static pressure probe 10, the airflow shielding structure 300, which protrudes from the collection end face 210 and is located outside the static pressure collection hole 212, can be located on the airflow path and shield the airflow for the static pressure collection hole 212. This allows for targeted adjustment of the airflow state near the static pressure collection hole 212, thereby changing the local airflow state near the static pressure collection hole 212 and consequently altering the static pressure collected by the static pressure collection hole 212.
[0044] When the aforementioned split static pressure probe 10 is applied to an aircraft, the airflow shielding structure 300 can change the local airflow state near the static pressure acquisition port 212, making some locations that previously did not meet the installation location requirements (locations with poor airflow stability) suitable for installation, thus reducing the requirements for the installation location. Furthermore, according to the attached... Figure 6 It is known that when the static pressure acquisition probes 10 are installed in the same position (both are installed on the side of the aircraft fuselage), the dimensionless static pressure data collected by the traditional static pressure acquisition probe 10 (without airflow obstruction structure 300 and its acquisition end face 210 not protruding from the outer surface of the aircraft body) will change significantly under different flight angles of attack. This data change will make the airspeed measurement inaccurate for the aircraft. However, the aforementioned static pressure acquisition probe 10 (at least part of the airflow obstruction structure 300 is exposed from the outer surface of the aircraft body and located on the windward side of the split static pressure probe 10) can change the local airflow state near the static pressure acquisition hole 212 because the airflow obstruction structure 300 can change the slope of the collected dimensionless static pressure data, thereby making the slope of the collected dimensionless static pressure data very flat (with very small changes). This allows the data provided to accurately measure the airspeed of the aircraft at different flight angles of attack. Moreover, the aforementioned static pressure acquisition probe 10 can change the average value of the collected dimensionless static pressure data, that is, it can reduce the average deviation of the originally collected data, so that the measurement data can be used directly without data correction. Therefore, the aforementioned split static pressure acquisition probe 10 can reduce the interference of installation position and aircraft attitude on the acquired data, thereby improving the stability and accuracy of the acquired data.
[0045] In this embodiment, the aforementioned split static pressure probe 10 is applied to an aircraft. It is understood that in other embodiments, the aforementioned split static pressure probe 10 can also be applied to other devices that require the acquisition of static pressure data.
[0046] In this embodiment, there are multiple static pressure acquisition holes 212. These holes are arranged at intervals. Having multiple static pressure acquisition holes 212, compared to having only one, not only improves the stability and accuracy of the acquired data but also effectively prevents the static pressure acquisition probe 10 from failing due to blockage of the holes. It is understood that in other embodiments, only one static pressure acquisition hole 212 may be used. Specifically, in this embodiment, there are five static pressure acquisition holes 212. These five holes are arranged at intervals in a cross shape. This further improves the stability and accuracy of the acquired data. It is understood that in other embodiments, there may also be three static pressure acquisition holes 212, or more than five.
[0047] In this embodiment, the airflow blocking structure 300 is an annular structure with a notch 310. Compared to a closed annular structure (without a notch 310), the annular structure with a notch 310 can prevent the accumulation of some particles, rainwater, etc., which can be discharged through the notch 310. It is understood that in other embodiments, the airflow blocking structure 300 may also be a closed annular structure.
[0048] In this embodiment, the notch angle α of the airflow blocking structure 300 is greater than 0° and less than or equal to 180°. Thus, the airflow blocking structure 300 can effectively block the airflow from the static pressure collection port 212. It can be understood that in other embodiments, when the airflow range of the application scenario is small, the notch angle α of the airflow blocking structure 300 can also be greater than 180°. Specifically, in this embodiment, the notch angle α of the airflow blocking structure 300 is 60°-120°. More specifically, in this embodiment, the notch angle α of the airflow blocking structure 300 is 90°.
[0049] In this embodiment, the height h of the airflow shielding structure 300 is 2-10 mm in the direction of the vertical acquisition end face 210. When at least a portion of the airflow shielding structure 300 is exposed from the outer surface of the aircraft body, the size of the airflow shielding structure 300 exposed from the outer surface of the aircraft body needs to be smaller than the boundary layer. The boundary layer, also called the flow boundary layer or boundary layer, has a low relative air velocity, and the exposed portion located within the boundary layer has virtually no impact on flight drag. By setting the height h of the airflow shielding structure 300 to 2-10 mm in the direction of the vertical acquisition end face 210, even if the airflow shielding structure 300 is entirely exposed from the outer surface of the aircraft body, it can be ensured that the exposed portion is located within the boundary layer, thereby preventing the airflow shielding structure 300 from affecting flight drag. Moreover, setting the height h of the airflow shielding structure 300 to 2-10 mm in the direction of the vertical acquisition end face 210 also allows the airflow shielding structure 300 to better shield the airflow. It can be understood that in other embodiments, the height h of the airflow shielding structure 300 can also be greater than 10 mm.
[0050] In this embodiment, the main structure 200 is cylindrical. The annular structure is a circular ring structure. The outer periphery of the annular structure near the acquisition end face 210 coincides with the outer periphery of the acquisition end face 210. This not only avoids the sharp edges of the aforementioned separate hydrostatic probe 10 from scratching the aircraft, but also prevents the annular structure from protruding beyond the outer periphery of the main structure 200 and interfering with other devices. It is understood that in other embodiments, the main structure 200 may also be square, and the annular structure may also be a square ring structure.
[0051] In this embodiment, the outer surface of the airflow blocking structure 300 has an inclined surface 320. The inclined surface 320 is inclined toward the static pressure collection port 212. The inclined surface 320 is set at an acute angle with the collection end face 210. The inclined surface 320 can guide the airflow, thereby making it easier for the airflow blocking structure 300 to change the local airflow state near the static pressure collection port 212. It can be understood that in other embodiments, the inclined surface 320 and the collection end face 210 can also be set perpendicularly, or the inclined surface 320 and the collection end face 210 can also be set at an obtuse angle.
[0052] In this embodiment, the acute angle is greater than or equal to 30°, that is, the complementary angle θ, which is complementary to the acute angle, is greater than 0° and less than or equal to 60°. This not only facilitates the guidance of airflow by the inclined plane 320, but also ensures that the airflow blocking structure 300 has good structural strength. It is understood that in other embodiments, the acute angle may be less than 30°.
[0053] In this embodiment, the main structure 200 also includes a static pressure output terminal 400. The static pressure output terminal 400 is located at the end of the main structure 200 away from the acquisition end face 210, and is used to output the acquired static pressure. This makes it very convenient to output the acquired static pressure.
[0054] In this embodiment, the detachable static pressure probe 10 further includes a mounting structure 500. The mounting structure 500 is disposed on the main body structure 200. Thus, the detachable static pressure probe 10 can be mounted on the aircraft body via the mounting structure 500. It is understood that in other embodiments, the mounting structure 500 may be omitted, in which case the detachable static pressure probe 10 can be mounted on the aircraft body via the main body structure 200.
[0055] In this embodiment, the mounting structure 500 is a closed-loop structure. The mounting structure 500 is fitted onto the circumferential direction of the main structure 200. The mounting structure 500 has a plurality of mounting through holes 510 arranged at intervals along the circumference. This facilitates the mounting of the aforementioned split hydrostatic probe 10 onto the aircraft body. It is understood that in other embodiments, the mounting structure 500 may also include a plurality of protrusions spaced apart along the circumference of the main structure 200.
[0056] This utility model also provides an aircraft. The aircraft includes an aircraft body and the aforementioned separate static pressure probe 10. The main structure 200 is disposed on the aircraft body. At least a portion of the airflow shielding structure 300 is exposed from the outer surface of the aircraft body and is located on the windward side of the separate static pressure probe 10.
[0057] In this embodiment, the airflow shielding structure 300 is entirely exposed on the outer surface of the aircraft body. This effectively shields the airflow while minimizing the height h of the airflow shielding structure 300.
[0058] In this embodiment, the size of the outer surface of the main structure 200 exposed on the aircraft body is smaller than that of the boundary layer.
[0059] In this embodiment, the main structure 200 is located on the side of the fuselage of the aircraft body.
[0060] In this embodiment, the aircraft body is the body of an electric vertical take-off and landing aircraft.
[0061] In this embodiment, when the airflow shielding structure 300 is an annular structure with a notch 310, the notch 310 is located on the leeward side of the airflow shielding structure 300.
[0062] In this embodiment, the surface perpendicular to the airflow direction is the first surface, which divides the airflow blocking structure 300 into a first semi-ring 330 and a second semi-ring 340. The first semi-ring 330 is located on the windward side of the split static pressure probe 10, and the second semi-ring 340 is located on the leeward side of the split static pressure probe 10. The second semi-ring 340 has a notch 310.
[0063] In this embodiment, the surface parallel to the airflow direction and perpendicular to the first surface is the second surface, which divides the airflow blocking structure 300 into a third and fourth semi-ring. The two azimuth angles determined by the two intersection points of the first surface and the airflow blocking structure 300 are +90° and -90°, respectively. The two azimuth angles determined by the two intersection points of the second surface and the airflow blocking structure 300 are +180° / -180° and 0°, respectively. 0° is located in the second semi-ring 340, and +180° / -180° is located in the first semi-ring 330. Thus, when the notch angle α is 0°-180°, the average notch azimuth angle β is -45°-45°. Figure 5 Taking the example shown, if one side of the notch angle α is at 0° and the other side is at 90°, then the notch angle α's degree range is 0°-90°, and the average notch azimuth angle β is (0°+90°) / 2, which is 45°. If the notch angle α's degree range is -30°-60°, then the average notch azimuth angle β is (-30°+60°) / 2, which is 15°.
[0064] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.
[0065] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of this patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.
Claims
1. A split-type hydrostatic probe, characterized in that, include: The main structure has a collection end face, and a static pressure collection hole is opened on the collection end face; as well as An airflow blocking structure protrudes from the collection end face and is located outside the static pressure collection hole to block the airflow from the static pressure collection hole.
2. The split hydrostatic probe as described in claim 1, characterized in that, The static pressure sampling holes are multiple, and the multiple static pressure sampling holes are arranged at intervals; and / or The height of the airflow shielding structure is 2-10mm in the direction perpendicular to the collection end face.
3. The split hydrostatic probe as described in claim 1, characterized in that, The airflow blocking structure is a closed ring structure or a ring structure with a gap.
4. The split hydrostatic probe as described in claim 3, characterized in that, The airflow blocking structure is a ring-shaped structure with a notch, and the notch angle of the airflow blocking structure is greater than 0° and less than or equal to 180°; and / or The main structure is cylindrical, and the annular structure is a circular ring structure. The outer periphery of the end face of the annular structure near the acquisition end face coincides with the outer periphery of the acquisition end face.
5. The split hydrostatic probe as described in claim 1, characterized in that, The outer side of the airflow shielding structure has a slope, which is inclined toward the static pressure collection hole and forms an acute angle with the collection end face.
6. The split hydrostatic probe as described in claim 5, characterized in that, The acute angle is greater than or equal to 30°.
7. The split hydrostatic probe as described in claim 1, characterized in that, The main structure also includes a static pressure output terminal, which is located at the end of the main structure away from the acquisition end face, for outputting the acquired static pressure; and / or The split static pressure probe also includes a mounting structure, which is located on the main structure.
8. The split hydrostatic probe as described in claim 1, characterized in that, There are five static pressure sampling holes, which are arranged at intervals in a cross shape; and / or The notch angle of the airflow shielding structure is 90°; and / or The separate static pressure probe also includes a mounting structure, which is a closed-loop structure. The mounting structure is sleeved on the circumference of the main structure and has multiple mounting through holes arranged at intervals along the circumference.
9. An aircraft, characterized in that, include: The aircraft itself; as well as The split static pressure probe as described in any one of claims 1-8, wherein the main structure is disposed on the aircraft body, and at least a portion of the airflow shielding structure is exposed from the outer surface of the aircraft body and located on the windward side of the split static pressure probe.
10. The aircraft as claimed in claim 9, characterized in that, The airflow shielding structure is entirely exposed from the outer surface of the aircraft body; and / or The airflow shielding structure exposed on the outer surface of the aircraft body has a dimension smaller than the boundary layer; and / or The main structure is located on the side of the fuselage of the aircraft body; and / or When the airflow blocking structure is a ring-shaped structure with a notch, a surface perpendicular to the airflow direction divides the airflow blocking structure into a first half-ring and a second half-ring. The first half-ring is located on the windward side of the split static pressure probe, and the second half-ring is located on the leeward side of the split static pressure probe. The notch is located on the second half-ring; and / or The aircraft body is the body of an electric vertical takeoff and landing aircraft.