Testing tool for atmospheric data sensor of certain type of airplane

Abstract

The utility model discloses a testing tool for an atmospheric data sensor of a certain type aircraft, which belongs to the field of testing tools and comprises a total pressure air inlet module and a static pressure air inlet module arranged opposite to the total pressure air inlet module, the total pressure air inlet module is detachably connected with the static pressure air inlet module, and the total pressure air inlet module is connected with the static pressure air inlet module. A notch is formed in the side face, facing the static pressure air inlet module, of the total pressure air inlet module, a first arc-shaped open groove is formed in the middle of the inner side face of the notch, a second arc-shaped open groove is formed in the middle of the inner side face of the first arc-shaped open groove, and a first groove hole is formed in the center of the side face, away from the static pressure air inlet module, of the total pressure air inlet module. The first slotted hole communicates with the second arc-shaped open groove, and a second slotted hole is formed in the center of the side face, facing the total pressure air inlet module, of the static pressure air inlet module. According to the utility model, the total pressure and the static pressure can be input through the tool, so that the atmospheric environment can be input when the atmospheric data sensor of a certain type of airplane is tested.

Description

Technical Field

[0001] This utility model relates to the field of testing fixtures, specifically a testing fixture for an atmospheric data sensor of a certain type of aircraft. Background Technology

[0002] The atmospheric data sensor is used to sense atmospheric static pressure, total pressure, etc., and outputs these values ​​to the atmospheric turbine for further calculation of atmospheric parameters such as barometric altitude, air velocity, Mach number, and altitude. Because the sensor's front end has an irregular structure, an atmospheric environment cannot be applied in the internal field, making performance testing impossible. Therefore, a specialized fixture needs to be designed to apply the atmospheric environment.

[0003] Therefore, those skilled in the art have provided a testing fixture for an aircraft air data sensor to solve the problems mentioned in the background art. Utility Model Content

[0004] The purpose of this invention is to provide a testing fixture for an air data sensor of a certain type of aircraft. This fixture enables the input of total pressure and static pressure, thereby enabling the input of the atmospheric environment during the testing of the air data sensor of a certain type of aircraft, thus solving the problems mentioned in the background art.

[0005] To achieve the above objectives, this utility model provides the following technical solution:

[0006] A test fixture for an air data sensor of a certain type of aircraft includes:

[0007] A total pressure intake module and a static pressure intake module disposed opposite to the total pressure intake module.

[0008] The total pressure intake module and the static pressure intake module are detachably connected.

[0009] As a further embodiment of this utility model: the total pressure intake module has a slot on one side facing the static pressure intake module, and a first arc-shaped slot is formed at the middle of the inner side of the slot, and a second arc-shaped slot is formed at the middle of the inner side of the first arc-shaped slot. The total pressure intake module has a first slot hole at the center of the side away from the static pressure intake module, and the first slot hole is connected to the second arc-shaped slot.

[0010] As a further embodiment of this utility model: the static pressure intake module has a second slot at the center of one side facing the total pressure intake module, and the second slot is aligned and matched with the first slot, and an annular groove is formed on the outside of the second slot.

[0011] As a further embodiment of this utility model: two parallel ear plates are symmetrically fixedly connected to both sides of the static pressure intake module, and a first screw hole is provided inside the ear plate. A second screw hole is provided on the side of the total pressure intake module facing the static pressure intake module, corresponding to the position of the first screw hole. The second screw hole is aligned and matched with the first screw hole. The total pressure intake module and the static pressure intake module are detachably connected by bolts inserted into the second screw hole and the first screw hole.

[0012] As a further embodiment of this utility model: a positioning plate is fixedly connected to the edge of the static pressure intake module facing the total pressure intake module, and a positioning groove is opened on the edge of the side of the total pressure intake module facing the static pressure intake module, and the positioning plate is inserted into the positioning groove and matches it.

[0013] Compared with the prior art, the beneficial effects of this utility model are:

[0014] 1. This application enables the input of total pressure and static pressure through this tooling, thereby enabling the input of atmospheric environment during the testing of an atmospheric data sensor for a certain type of aircraft. Attached Figure Description

[0015] Figure 1 A schematic diagram of the structure of a test fixture for an atmospheric data sensor of a certain type of aircraft;

[0016] Figure 2 This is a schematic diagram of the static pressure intake module in the testing fixture for an atmospheric data sensor of a certain type of aircraft.

[0017] Figure 3 This is a schematic diagram of the total pressure intake module in the testing fixture for an air data sensor of a certain type of aircraft.

[0018] In the diagram: 1. Total pressure intake module; 2. Static pressure intake module; 3. Second slot; 4. Annular slot; 5. Slot opening; 6. First arc-shaped slot; 7. Second arc-shaped slot; 8. First slot; 9. Ear plate; 10. First screw hole; 11. Second screw hole; 12. Positioning slot; 13. Positioning 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. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0020] As mentioned in the background section of this application, the inventor has discovered through research that the existing sensor front end adopts an irregular structure, which makes it impossible to apply an atmospheric environment to the internal field and conduct performance tests, thus having certain defects.

[0021] To address the aforementioned deficiencies, this application discloses a testing fixture for an air data sensor of a certain type of aircraft. This fixture enables the input of total pressure and static pressure, thereby facilitating the input of the atmospheric environment during the testing of the air data sensor of a certain type of aircraft.

[0022] The following will describe in detail, with reference to the accompanying drawings, how the solution of this application solves the above-mentioned technical problems.

[0023] Please see Figures 1-3 In this embodiment of the invention, a test fixture for an aircraft air data sensor includes: a total pressure intake module 1 and a static pressure intake module 2 disposed opposite to the total pressure intake module 1, wherein the total pressure intake module 1 and the static pressure intake module 2 are detachably connected. This fixture enables the input of total pressure and static pressure, thereby facilitating the input of the atmospheric environment during the testing of an aircraft air data sensor.

[0024] In this embodiment, the total pressure intake module 1 has a slot 5 on one side facing the static pressure intake module 2, and a first arc-shaped slot 6 is formed at the middle of the inner side of the slot 5. A second arc-shaped slot 7 is formed at the middle of the inner side of the first arc-shaped slot 6. A first slot hole 8 is formed at the center of the side of the total pressure intake module 1 away from the static pressure intake module 2, and the first slot hole 8 communicates with the second arc-shaped slot 7. The total pressure intake module 1 can be connected to the total pressure pipeline of an external atmospheric pressure testing instrument to realize the input of total pressure.

[0025] In this embodiment, the static pressure intake module 2 has a second slot 3 at its center on one side facing the total pressure intake module 1, and the second slot 3 is aligned and matched with the first slot 8. An annular groove 4 is formed on the outside of the second slot 3. The static pressure intake module 2 can be connected to the static pressure pipeline of an external atmospheric pressure testing instrument to realize static pressure input.

[0026] In this embodiment, two parallel ear plates 9 are symmetrically fixedly connected to both sides of the static pressure intake module 2, and a first screw hole 10 is provided inside the ear plate 9. A second screw hole 11 is provided on the side of the total pressure intake module 1 facing the static pressure intake module 2, corresponding to the position of the first screw hole 10. The second screw hole 11 is aligned and matched with the first screw hole 10. The total pressure intake module 1 and the static pressure intake module 2 are detachably connected by bolts inserted into the second screw hole 11 and the first screw hole 10. This arrangement facilitates the disassembly and connection of the total pressure intake module 1 and the static pressure intake module 2.

[0027] In this embodiment, a positioning plate 13 is fixedly connected to the edge of one side of the static pressure intake module 2 facing the total pressure intake module 1, and a positioning groove 12 is provided on the edge of one side of the total pressure intake module 1 facing the static pressure intake module 2. The positioning plate 13 is inserted into the positioning groove 12 and matches it. The cooperation between the positioning plate 13 and the positioning groove 12 enables rapid alignment when the total pressure intake module 1 and the static pressure intake module 2 are docked.

[0028] The working principle of this utility model is as follows: During use, the target atmospheric data sensor is placed into the slot 5 of the total pressure intake module 1. During this process, the total pressure intake module 1 is brought into contact with the total pressure intake surface of the target atmospheric data sensor. Rubber pads are placed in the first arc-shaped slot 6 and the second arc-shaped slot 7 at the contact point to enhance airtightness. Then, the first slot 8 is connected to the total pressure pipeline of an external atmospheric testing instrument to apply the required total pressure environment for testing. The static pressure intake module 2 is brought into contact with the static pressure intake surface of the target atmospheric data sensor. A rubber ring is used in the annular groove 4 at the contact point to enhance airtightness. Then, the second slot 3 is connected to the static pressure pipeline of an external atmospheric testing instrument to apply the required static pressure environment for testing. Finally, the total pressure intake module 1 and the static pressure intake module 2 are connected by bolts inserted into the four threaded holes of the positioning plate 13 to ensure a firm and reliable connection. In summary, this fixture can achieve the input of total pressure and static pressure, thereby enabling the input of the atmospheric environment for testing an atmospheric data sensor of a certain type of aircraft.

[0029] Obviously, those skilled in the art can make various modifications and variations to this utility model without departing from its spirit and scope. Therefore, if these modifications and variations fall within the scope of the claims of this utility model and their equivalents, this utility model also intends to include these modifications and variations.

[0030] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model, based on the technical solution and the inventive concept of the present utility model, should be included within the protection scope of the present utility model.

Claims

1. An aircraft air data sensor testing tool, characterized in that, The utility model relates to a total pressure air intake module (1) and a static pressure air intake module (2) arranged opposite to the total pressure air intake module (1). The total pressure air intake module (1) is detachably connected with the static pressure air intake module (2). The side of the total pressure air intake module (1) facing the static pressure air intake module (2) is provided with a notch (5), and the inner side of the notch (5) is provided with a first arc-shaped slot (6) at the middle position, the inner side of the first arc-shaped slot (6) is provided with a second arc-shaped slot (7) at the middle position, and the side of the total pressure air intake module (1) away from the static pressure air intake module (2) is provided with a first slot hole (8) at the center, and the first slot hole (8) is in communication with the second arc-shaped slot (7).

2. The test tool for pitot-static sensors of claim 1, wherein, The side of the static pressure air intake module (2) facing the total pressure air intake module (1) is provided with a second slot hole (3) at the center, and the second slot hole (3) is aligned with and matched with the first slot hole (8), and the outer side of the second slot hole (3) is provided with an annular groove (4).

3. The test tool for pitot-static sensors of claim 2, wherein, The two sides of the static pressure air intake module (2) are symmetrically and fixedly connected with two parallel ear plates (9), and the inner side of the ear plate (9) is provided with a first screw hole (10), the side of the total pressure air intake module (1) facing the static pressure air intake module (2) is provided with a second screw hole (11) at the position corresponding to the first screw hole (10), and the second screw hole (11) is aligned with and matched with the first screw hole (10), and the total pressure air intake module (1) and the static pressure air intake module (2) are detachably connected through the bolts implanted in the second screw hole (11) and the first screw hole (10).

4. The test tool for pitot-static sensors of claim 3, wherein, The side of the static pressure air intake module (2) facing the total pressure air intake module (1) is fixedly connected with a positioning plate (13) at the edge position, and the side of the total pressure air intake module (1) facing the static pressure air intake module (2) is provided with a positioning groove (12) at the edge position, and the positioning plate (13) is matched with the positioning groove (12) by being clamped into the positioning groove (12).

5. The aircraft pitot-static probe testing tool of claim 4, wherein: ​

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