Guide pipe connecting device for airplane dragging measuring device

Abstract

The utility model relates to the technical field of aircraft airspeed calibration technology, in particular to a conduit connecting device for an aircraft dragging measuring device, which comprises a fixing plate and a connecting component, the fixing plate is suitable for being mounted in a projectile body connected with an aircraft and used for measuring air pressure, one end of the fixing plate is fixedly connected with the inner wall of the projectile body, and the other end of the fixing plate is fixedly connected with the connecting component. A plurality of connecting pieces are arranged at the other end of the fixing plate at intervals in the length direction of the fixing plate, one ends of the connecting pieces are hinged to the fixing plate, the other ends of the connecting pieces are detachably connected with the corresponding ends of the fixing plate through bolts, and static-pressure air-entraining guide pipes are fixed between the connecting pieces and the fixing plate; one end of the connecting assembly communicates with a plurality of static pressure measuring holes formed in the side wall of the projectile body, the other end of the connecting assembly communicates with the static pressure air guiding pipe, and the end, away from the connecting assembly, of the static pressure air guiding pipe penetrates through the projectile body to be connected with a sensor in an airplane. And the flexibility and the accuracy of measurement are improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft airspeed calibration technology, in particular to a catheter connecting device for an aircraft drag measuring device. Background Art

[0002] In the aviation field, aircraft performance testing and evaluation are key steps to ensure their safe operation and efficient performance. Among them, gas pressure measurement is one of the important means to evaluate the aerodynamic characteristics of aircraft. Gas pressure is mainly divided into total pressure and static pressure. Total pressure refers to the pressure when the airflow hits an object, while static pressure is the pressure of the gas when it is not affected by the flow rate. The measurement of these two pressures is crucial to understanding the airflow conditions around the aircraft.

[0003] Traditional methods of measuring gas pressure usually involve mounting the measuring device directly on the surface of the aircraft or dragging it into the airflow behind the aircraft. These devices, especially the towed projectiles (or probes), need to accurately measure the total and static pressures of the gas. To achieve this, the projectiles are equipped with a special duct system to guide the gas to the pressure sensor.

[0004] In terms of static pressure measurement, since data needs to be obtained from multiple directions to accurately reflect the static pressure state of the gas, multiple static pressure holes are set on the missile body. These static pressure holes are connected to the pressure sensor through the internal static pressure air duct. However, this design has some challenges. First, the layout of multiple static pressure holes and ducts needs to be carefully planned to ensure that each hole can effectively capture the static pressure and will not interfere with each other. Second, the static pressure air duct needs to be properly fixed inside the missile body to prevent displacement or damage due to vibration or airflow impact during flight. Utility Model Content

[0005] In view of this, the present invention aims at the deficiencies of the prior art and proposes a catheter connecting device for an aircraft drag measuring device, aiming to solve at least one of the problems raised by the above-mentioned background technology.

[0006] The utility model provides a duct connection device for an aircraft drag measurement device, comprising: a fixing plate, which is suitable for being installed inside a bomb connected to an aircraft and used to measure air pressure, one end of the fixing plate is fixedly connected to the inner wall of the bomb, the other end of the fixing plate is provided with a plurality of connecting pieces at intervals along the length direction of the fixing plate, one end of the connecting piece is hinged to the fixing plate, the other end of the connecting piece is detachably connected to the corresponding end of the fixing plate by a bolt, and the static pressure bleed duct is fixed between the connecting piece and the fixing plate;

[0007] A connecting component, one end of which is connected to a plurality of static pressure measuring holes arranged on the side wall of the missile body, and the other end of which is connected to the static pressure air duct. The static pressure air duct is connected to a sensor in the aircraft through the missile body away from one end of the connecting component.

[0008] In some embodiments, the axial cross-section of the fixing plate is a rectangular structure.

[0009] In some embodiments, a groove matching the outer diameter of the static pressure air duct is provided at one end of the fixing plate away from the inner wall of the projectile along the axial centerline of the length direction of the fixing plate, and a first connecting plate is fixedly connected to one end of the fixing plate away from the hinged end of the connecting piece.

[0010] In some embodiments, the connecting member is an arc-shaped plate whose one side is adapted to the outer diameter of the static pressure airway duct, one end of the arc-shaped plate is hinged to the fixed plate, and the other end of the arc-shaped plate is fixedly connected to a second connecting plate adapted to the first connecting plate.

[0011] In some embodiments, the first connecting plate and the second connecting plate are both correspondingly provided with through holes for bolts to pass through.

[0012] In some embodiments, the static pressure air duct is provided with multiple first connecting tubes in a circular array corresponding to multiple static pressure measuring holes near one end of the static pressure measurement hole, and one end of the multiple first connecting tubes is connected to the multiple static pressure measurement holes respectively, and the other ends of the multiple first connecting tubes are connected to the static pressure air duct.

[0013] In some embodiments, each of the first connecting tubes is provided with an electric closer, and the electric closer is electrically connected to a controller inside the aircraft.

[0014] In some embodiments, the electric closer is disposed at one end of the first connecting tube close to the static pressure airway catheter.

[0015] Compared with the prior art, the beneficial effect of the utility model lies in that a fixing plate is used to stabilize the static pressure air duct, and an electric closer is used to control the connection or closure of the connecting pipe. This design allows the use of the static pressure hole to be dynamically adjusted according to actual measurement needs, thereby improving the flexibility and accuracy of the measurement. The use of the electric closer also means that the opening and closing of the static pressure hole can be managed by remote control or an automated system, further improving the convenience of operation and the response speed of the system. The use of the fixing plate can ensure that the position of the static pressure air duct is stable and unchanged, which helps to maintain the alignment between the duct and the static pressure hole, thereby ensuring the accurate transmission of the static pressure to the sensor. The aircraft will vibrate during flight, and the fixing plate can provide stable support for the static pressure air duct, reduce the movement or damage of the duct caused by vibration, thereby ensuring the accuracy and consistency of the measurement data.

[0016] The foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present disclosure.

[0017] Other features and aspects of the present disclosure will become more apparent from the following detailed description of exemplary embodiments with reference to the attached drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the specific implementation methods of the utility model or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0019] Figure 1 A front view of a conduit connection device for an aircraft drag measurement device provided by an embodiment of the utility model;

[0020] Figure 2 A front view of a fixing plate of a conduit connection device for an aircraft drag measuring device provided by an embodiment of the utility model;

[0021] Figure 3 A front view of a connecting assembly of a conduit connecting device for an aircraft drag measuring device provided by an embodiment of the utility model;

[0022] Figure 4 A diagram showing a fixing plate of a conduit connection device for an aircraft drag measuring device provided in an embodiment of the utility model.

[0023] Among them: 1. fixing plate; 2. connecting piece; 3. static pressure air duct; 4. connecting assembly; 5. groove; 6. first connecting plate; 7. arc plate; 8. second connecting plate; 9. first connecting pipe; 10. electric closer. DETAILED DESCRIPTION

[0024] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0025] In the description of the present application, it should be understood that the terms "center", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0026] The terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, unless otherwise specified, "plurality" means two or more.

[0027] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0028] As mentioned in the background technology, in terms of static pressure measurement, since data needs to be obtained from multiple directions to accurately reflect the static pressure state of the gas, multiple static pressure holes are set on the projectile, and these static pressure holes are connected to the pressure sensor through the internal static pressure air duct. However, this design has some challenges. First, the layout of multiple static pressure holes and ducts needs to be carefully planned to ensure that each hole can effectively capture the static pressure and will not interfere with each other. Secondly, the static pressure air duct needs to be properly fixed inside the projectile to prevent displacement or damage due to vibration or airflow impact during flight.

[0029] In order to improve the above-mentioned problems, the present application proposes a duct connecting device for an aircraft drag measurement device, which adopts a fixing plate to stabilize the static pressure air duct, and controls the connection or closure of the connecting pipe through an electric closer. This design allows the use of the static pressure hole to be dynamically adjusted according to the actual measurement needs, thereby improving the flexibility and accuracy of the measurement. The use of the electric closer also means that the opening and closing of the static pressure hole can be managed by remote control or an automated system, further improving the convenience of operation and the response speed of the system. The use of the fixing plate can ensure that the position of the static pressure air duct is stable and unchanged, which helps to maintain the alignment between the duct and the static pressure hole, thereby ensuring the accurate transmission of the static pressure to the sensor. The aircraft will vibrate during flight, and the fixing plate can provide stable support for the static pressure air duct, reduce the movement or damage of the duct caused by vibration, thereby ensuring the accuracy and consistency of the measurement data.

[0030] See also Figure 1-4 As shown, a catheter connecting device for an aircraft drag measuring device according to an embodiment of the present application includes:

[0031] A fixing plate 1 is suitable for being installed inside a bomb connected to an aircraft for measuring air pressure. One end of the fixing plate 1 is fixedly connected to the inner wall of the bomb. The other end of the fixing plate 1 is provided with a plurality of connecting members 2 at intervals along the length direction of the fixing plate 1. One end of the connecting member 2 is hinged to the fixing plate 1. The other end of the connecting member 2 is detachably connected to the corresponding end of the fixing plate 1 by bolts. A static pressure bleed duct 3 is fixed between the connecting member 2 and the fixing plate 1.

[0032] The connecting component 4 has one end connected to a plurality of static pressure measuring holes arranged on the side wall of the missile body, and the other end connected to the static pressure air duct 3. The static pressure air duct 3 is connected to the sensor in the aircraft through the end away from the connecting component 4.

[0033] In some specific embodiments, the axial cross-section of the fixing plate 1 is a rectangular structure.

[0034] In some specific embodiments, a groove 5 adapted to the outer diameter of the static pressure air duct 3 is provided at one end of the fixing plate 1 away from the inner wall of the projectile along the axial centerline of the length direction of the fixing plate 1, and a first connecting plate 6 is fixedly connected to one end of the fixing plate 1 away from the hinged end with the connecting piece 2.

[0035] In some specific embodiments, the connecting member 2 is an arc-shaped plate 7 whose one side is adapted to the outer diameter of the static pressure airway 3, one end of the arc-shaped plate 7 is hinged to the fixed plate 1, and the other end of the arc-shaped plate 7 is fixedly connected to a second connecting plate 8 adapted to the first connecting plate 6.

[0036] In some specific embodiments, the first connecting plate 6 and the second connecting plate 8 are both correspondingly provided with through holes for bolts to pass through.

[0037] It should be understood that the static pressure air duct 3 is arranged in the groove 5 and abuts against the inner wall of the groove 5. The static pressure air duct is fixed by the arc plate 7 and is detachably connected to the first connecting plate 6 and the second connecting plate 8 by bolts.

[0038] In some specific embodiments, a plurality of first connecting tubes 9 are provided in a circular array corresponding to a plurality of static pressure measuring holes near one end of the static pressure duct 3 close to the static pressure measuring hole, and one end of the plurality of first connecting tubes 9 is respectively connected to the plurality of static pressure measuring holes, and the other ends of the plurality of first connecting tubes 9 are all connected to the static pressure duct 3.

[0039] In some specific embodiments, each of the plurality of first connecting tubes 9 is provided with an electric closer 10 , and the electric closer 10 is electrically connected to a controller inside the aircraft.

[0040] It should be understood that by arranging the electric closer 10 on the first connecting pipe 9, the electric closer 10 can be controlled according to actual needs to close the corresponding first connecting pipe 9 and directly connect the static pressure measurement hole that needs to be connected, or all the first connecting pipes 9 can be connected at the same time to measure all static pressures.

[0041] In some specific embodiments, the electric closer 10 is disposed at one end of the first connecting tube 9 close to the static pressure bleed duct 3 .

[0042] Obviously, those skilled in the art can make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these modifications and variations.

Claims

1. A catheter connection device for an aircraft drag measurement device, characterized in that: include: A fixing plate, which is suitable for being installed inside a bomb connected to an aircraft for measuring air pressure, wherein one end of the fixing plate is fixedly connected to the inner wall of the bomb, and the other end of the fixing plate is provided with a plurality of connecting pieces at intervals along the length direction of the fixing plate, wherein one end of the connecting piece is hinged to the fixing plate, and the other end of the connecting piece is detachably connected to the corresponding end of the fixing plate by bolts, and the static pressure bleed duct is fixed between the connecting piece and the fixing plate; A connecting component, one end of which is connected to a plurality of static pressure measuring holes arranged on the side wall of the missile body, and the other end of which is connected to the static pressure air duct. The static pressure air duct is connected to a sensor in the aircraft through the missile body away from one end of the connecting component.

2. A catheter connection device for an aircraft drag measurement device according to claim 1, characterized in that: The axial cross section of the fixing plate is a rectangular structure.

3. A catheter connection device for an aircraft drag measurement device according to claim 2, characterized in that: A groove matching the outer diameter of the static pressure air duct is arranged at one end of the fixing plate away from the inner wall of the projectile along the axial centerline in the length direction of the fixing plate, and a first connecting plate is fixedly connected to one end of the fixing plate away from the hinged end of the connecting piece.

4. A catheter connection device for an aircraft drag measurement device according to claim 3, characterized in that: The connecting piece is an arc-shaped plate whose one side is matched with the outer diameter of the static pressure air duct, one end of the arc-shaped plate is hinged to the fixed plate, and the other end of the arc-shaped plate is fixedly connected with a second connecting plate matched with the first connecting plate.

5. The catheter connection device for an aircraft drag measurement device according to claim 4, characterized in that: The first connecting plate and the second connecting plate are both correspondingly provided with through holes for bolts to pass through.

6. The catheter connection device for an aircraft drag measurement device according to claim 1, characterized in that: The static pressure air duct is provided with a plurality of first connecting tubes in a circular array corresponding to the plurality of static pressure measuring holes at one end close to the static pressure measuring hole, and the plurality of first connecting tubes are connected to the static pressure air duct at one end corresponding to the plurality of static pressure measuring holes, and the other ends of the plurality of first connecting tubes are connected to the static pressure air duct.

7. A catheter connection device for an aircraft drag measurement device according to claim 6, characterized in that: Each of the first connecting pipes is provided with an electric closer, and the electric closer is electrically connected to a controller inside the aircraft.

8. The catheter connection device for an aircraft drag measurement device according to claim 7, characterized in that: The electric closer is arranged at one end of the first connecting pipe close to the static pressure air duct.

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