Flow field probe positioning control device for aerospace craft

Abstract

The utility model relates to the technical field of aerospace, in particular to a flow field probe positioning control device for an aerospace craft, which comprises a mounting block mounted on a wing of the aerospace craft, a miniature five-hole probe anemograph is arranged on one side of the mounting block, and the miniature five-hole probe anemograph is arranged on the other side of the mounting block. The interior of the mounting block is connected with the miniature five-hole probe anemograph through a movable positioning mechanism, the top of the mounting block is symmetrically and fixedly connected with L-shaped mounting plates, and mounting holes are symmetrically formed in the tops of the mounting plates. Through the cooperation of a screw rod and a moving rod, the movement of the position of the miniature five-hole probe anemograph can be controlled, through the cooperation of a second miniature servo motor and a rotating shaft, the direction of the miniature five-hole probe anemograph can be adjusted through rotation, and the miniature five-hole probe anemograph can be moved and positioned to a position needing to be measured. And diversified measurement requirements can be met, so that accurate evaluation of the aerodynamic performance of the aircraft can be ensured.

Description

Technical Field

[0001] This utility model relates to the field of aerospace technology, and in particular to a flow field probe positioning and control device for aerospace vehicles. Background Technology

[0002] In the aerospace field, flow field probes, as key aerodynamic measurement tools, are widely used in the design and testing phases of aircraft. These probes capture crucial parameters such as pressure and velocity in the flow field surrounding the aircraft, providing valuable data support for aerodynamic performance evaluation, stability analysis, and flight safety verification. Particularly in the development of aircraft operating at high speeds and in complex aerodynamic environments, such as supersonic aircraft, hypersonic vehicles, and various missiles, the measurement data from flow field probes is essential for ensuring that the aircraft meets performance standards and ensures flight safety.

[0003] Although flow field probes play an irreplaceable role in the development of aerospace vehicles, their positioning methods have certain limitations. Traditional methods for fixing the position of flow field probes often use mechanical connections or adhesives to firmly install the probes at predetermined positions on the aircraft. However, it is difficult to effectively adjust the position and orientation of the probes to adapt to diverse measurement needs, thus affecting the accurate assessment of the aerodynamic performance of the aircraft. Therefore, a flow field probe positioning and control device for aerospace vehicles is proposed. Utility Model Content

[0004] The purpose of this invention is to address the shortcomings of existing technologies where fixed-position probes are difficult to adjust effectively to meet diverse measurement needs, thus affecting the accurate assessment of aircraft aerodynamic performance. Therefore, this invention proposes a flow field probe positioning and control device for aerospace vehicles.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] A flow field probe positioning and control device for aerospace vehicles includes a mounting block installed on the wing of the aerospace vehicle. A miniature five-hole probe anemometer is provided on one side of the mounting block, and an internal device on the mounting block is connected to the miniature five-hole probe anemometer via a moving positioning mechanism.

[0007] Preferably, the top of the mounting block is symmetrically fixedly connected with an L-shaped mounting plate, and the top of the mounting plate is symmetrically provided with mounting holes.

[0008] Preferably, the mobile positioning mechanism includes a first micro servo motor, a screw, and a moving rod. The mounting block has a rectangular cross-section moving cavity inside, and a moving opening communicating with the inside of the moving cavity is opened on one side of the mounting block. The first micro servo motor is fixedly connected to the inner wall of the moving cavity, and the output end of the first micro servo motor is connected to the screw. The moving rod has a threaded groove on the side near the first micro servo motor, and the screw is threadedly connected to the threaded groove. A connecting block is fixedly connected to one end of the moving rod, and a second micro servo motor is fixedly installed inside the connecting block. A rotating shaft is provided at the output end of the second micro servo motor, and one end of the rotating shaft is fixedly connected to the micro five-hole probe anemometer.

[0009] Preferably, a rectangular frame is fixedly connected to the outer wall of the moving rod located inside the moving cavity, and the outer wall of the rectangular frame is slidably connected to the inner wall of the moving cavity.

[0010] Preferably, a sealing ring is fixedly connected to the inner wall of the movable port, and the outer wall of the movable rod is slidably connected to the inner wall of the sealing ring.

[0011] Preferably, the outer wall of the movable rod has a first arc-shaped rounded corner that is equidistant from the circumference, the outer wall of the mounting block has a second arc-shaped rounded corner that is equidistant from the circumference, and the outer wall of the connecting block has a third arc-shaped rounded corner that is equidistant from the circumference.

[0012] Preferably, one end of the miniature five-hole probe anemometer has multiple probe holes.

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

[0014] When in use, this device utilizes a mobile positioning mechanism. Through the cooperation of a screw and a moving rod, the position of the miniature five-hole probe anemometer can be controlled. Furthermore, through the cooperation of a second miniature servo motor and a rotating shaft, the direction of the miniature five-hole probe anemometer can be adjusted by rotation. The miniature five-hole probe anemometer can be moved and positioned to the location that needs to be measured, thus adapting to diverse measurement needs and ensuring accurate assessment of the aerodynamic performance of aircraft. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the external three-dimensional structure of a flow field probe positioning and control device for aerospace vehicles proposed in this utility model.

[0016] Figure 2 This is a three-dimensional structural diagram of a flow field probe positioning and control device for aerospace vehicles proposed in this utility model.

[0017] Figure 3This is a schematic diagram of the connection structure of the mobile positioning mechanism.

[0018] In the diagram: 1. Mounting block; 2. Miniature five-hole probe anemometer; 3. Mounting plate; 4. Mounting hole; 5. First miniature servo motor; 6. Screw; 7. Moving rod; 8. Moving cavity; 9. Moving port; 10. Threaded groove; 11. Connecting block; 12. Second miniature servo motor; 13. Rectangular frame; 14. Sealing ring; 15. First arc-shaped fillet; 16. Second arc-shaped fillet; 17. Third arc-shaped fillet. 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 1-3 A flow field probe positioning and control device for aerospace vehicles includes a mounting block 1 installed on the wing of the aerospace vehicle. A miniature five-hole probe anemometer 2 is provided on one side of the mounting block 1. The internal part of the mounting block 1 is connected to the miniature five-hole probe anemometer 2 through a moving positioning mechanism.

[0021] It should be noted that the specific models and specifications of the miniature five-hole probe anemometer 2, the first miniature servo motor 5, and the second miniature servo motor 12 need to be selected and determined according to the actual specifications of the device. The specific selection calculation method adopts the existing technology in this field, so it will not be described. All of them can be powered by external devices and controlled to turn on and off. At the same time, the installation of the first miniature servo motor 5 and the second miniature servo motor 12 is the existing technology and can be installed and fixed according to the actual situation.

[0022] Furthermore, L-shaped mounting plates 3 are symmetrically fixedly connected to the top of the mounting block 1. Mounting holes 4 are symmetrically opened on the top of the mounting plate 3. It should be noted that corresponding fixing blocks are fixed on the wings of aerospace vehicles. Threaded grooves 10 are symmetrically opened on the bottom of the fixing blocks. Washers are then inserted into bolts, and bolts are inserted into mounting holes 4 and screwed into threaded grooves 10. This allows the miniature five-hole probe anemometer 2 to be fixed on the wing. The installation and fixing of the miniature five-hole probe anemometer 2 is generally existing technology and can be installed and fixed according to the actual situation.

[0023] Furthermore, the mobile positioning mechanism includes a first micro servo motor 5, a screw 6, and a moving rod 7. The mounting block 1 has a rectangular cross-section moving cavity 8 inside, and a moving opening 9 through the moving cavity 8 is opened on one side of the mounting block 1. The first micro servo motor 5 is fixedly connected to the inner wall of the moving cavity 8, and the output end of the first micro servo motor 5 is connected to the screw 6. The moving rod 7 has a threaded groove 10 on the side near the first micro servo motor 5, and the screw 6 is threadedly connected to the threaded groove 10. It should be noted that the first micro servo motor 5 can control the rotation of the screw 6, and the screw 6 will control the movement of the moving rod 7 through the threaded groove 10. The moving rod 7 will control the position movement of the micro five-hole probe anemometer 2.

[0024] One end of the moving rod 7 is fixedly connected to a connecting block 11. A second micro servo motor 12 is fixedly installed inside the connecting block 11. The output end of the second micro servo motor 12 is provided with a rotating shaft. One end of the rotating shaft is fixedly connected to the micro five-hole probe anemometer 2. It should be noted that the second micro servo motor 12 controls the rotation adjustment of the micro five-hole probe anemometer 2 through the rotating shaft, so as to adjust the measurement direction of the micro five-hole probe anemometer 2.

[0025] Furthermore, a rectangular frame 13 is fixedly connected to the outer wall of the moving rod 7 located inside the moving cavity 8. The outer wall of the rectangular frame 13 is slidably connected to the inner wall of the moving cavity 8. It should be noted that by limiting the sliding between the rectangular frame 13 and the moving cavity 8, not only can the moving rod 7 move stably, but it can also prevent the moving rod 7 from moving out of the moving cavity 8.

[0026] Furthermore, a sealing ring 14 is fixedly connected to the inner wall of the movable port 9, and the outer wall of the movable rod 7 is slidably connected to the inner wall of the sealing ring 14. It should be noted that the sealing ring 14 can prevent air from entering the interior of the movable cavity 8.

[0027] Furthermore, the outer wall of the moving rod 7 is provided with a first arc-shaped rounded corner 15 that is equidistantly distributed around the circumference, the outer wall of the mounting block 1 is provided with a second arc-shaped rounded corner 16 that is equidistantly distributed around the circumference, and the outer wall of the connecting block 11 is provided with a third arc-shaped rounded corner 17 that is equidistantly distributed around the circumference. It should be noted that by setting the first arc-shaped rounded corner 15, the second arc-shaped rounded corner 16, and the third arc-shaped rounded corner 17, the resistance can be reduced.

[0028] Furthermore, the miniature five-hole probe anemometer 2 has multiple probe holes at one end. It should be noted that airflow will continuously pass through or enter the probe holes, so that the miniature five-hole probe anemometer 2 can test the required data.

[0029] Working principle of this utility model:

[0030] First, the miniature five-hole probe anemometer 2 can be fixedly mounted on the wing by inserting bolts into the mounting holes 4 on the mounting plate 3 and screwing them into the predetermined position on the wing of the aerospace vehicle.

[0031] Then, the first micro servo motor 5 can control the screw 6 to rotate, and the screw 6 will control the movement of the moving rod 7 through the threaded groove 10. The moving rod 7 will control the position movement of the micro five-hole probe anemometer 2.

[0032] Finally, the second micro servo motor 12 controls the rotation adjustment of the micro five-hole probe anemometer 2 through the rotating shaft, which can adjust the measurement direction of the micro five-hole probe anemometer 2.

[0033] 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. A flow field probe positioning control device for aerospace vehicles, comprising a mounting block (1) mounted on the wing of an aerospace vehicle, characterized in that, One side of the mounting block (1) is provided with a micro five-hole probe anemometer (2), and the inside of the mounting block (1) is connected with the micro five-hole probe anemometer (2) through a moving positioning mechanism.

2. A flowfield probe positioning control apparatus for an aerospace vehicle as recited in claim 1, wherein, The top of the mounting block (1) is fixedly connected with an L-shaped mounting plate (3) in a symmetrical manner, and the top of the mounting plate (3) is symmetrically provided with mounting holes (4).

3. A flowfield probe positioning control apparatus for an aerospace vehicle as recited in claim 1, wherein, The moving positioning mechanism comprises a first micro servo motor (5), a screw rod (6) and a moving rod (7), the inside of the mounting block (1) is provided with a moving cavity (8) with a rectangular cross section, one side of the mounting block (1) is provided with a moving port (9) penetrating through the inside of the moving cavity (8), the first micro servo motor (5) is fixedly connected with the inner wall of the moving cavity (8), the output end of the first micro servo motor (5) is connected with the screw rod (6), one side of the moving rod (7) close to the first micro servo motor (5) is provided with a threaded groove (10), the screw rod (6) is threadedly connected with the threaded groove (10), one end of the moving rod (7) is fixedly connected with a connecting block (11), the inside of the connecting block (11) is fixedly provided with a second micro servo motor (12), the output end of the second micro servo motor (12) is provided with a rotating shaft, one end of the rotating shaft is fixedly connected with the micro five-hole probe anemometer (2).

4. A flowfield probe positioning control apparatus for an aerospace vehicle as recited in claim 3, wherein, The outer wall of the moving rod (7) located in the moving cavity (8) is fixedly connected with a rectangular frame (13), and the outer wall of the rectangular frame (13) is slidably connected with the inner wall of the moving cavity (8).

5. A flowfield probe positioning control apparatus for an aerospace vehicle as recited in claim 3, wherein, The inner wall of the moving port (9) is fixedly connected with a sealing ring (14), and the outer wall of the moving rod (7) is slidably connected with the inner wall of the sealing ring (14).

6. A flowfield probe positioning control apparatus for an aerospace vehicle as recited in claim 1, wherein, The outer wall of the moving rod (7) is provided with first arc-shaped fillets (15) distributed at equal intervals in a circumferential direction, the outer wall of the mounting block (1) is provided with second arc-shaped fillets (16) distributed at equal intervals in a circumferential direction, and the outer wall of the connecting block (11) is provided with third arc-shaped fillets (17) distributed at equal intervals in a circumferential direction.

7. The flowfield probe positioning control apparatus for an aerospace vehicle of claim 1, wherein, One end of the micro five-hole probe anemometer (2) is provided with a plurality of probe holes.

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