Standby static pressure source rotary switch structure for simulating aircraft

Abstract

The utility model discloses a simulation aircraft standby static pressure source rotary switch structure, which comprises a main shaft, an upper layer plate and a lower layer plate, round holes are arranged at corresponding positions in the middle of the upper layer plate and the lower layer plate, an oil-free bushing is embedded in each round hole, the main shaft sequentially penetrates through the round holes arranged at the middle positions of the upper layer plate and the lower layer plate from top to bottom, and the oil-free bushing is embedded in the oil-free bushing. The top of the main shaft is connected with a rotating handle, the main shaft is in threaded connection with a self-locking nut at the thread position below the upper-layer plate, and the main shaft below the self-locking nut is sequentially sleeved with a flat gasket, four disc springs, a friction plate and a fluorine rubber ring from top to bottom; the part, located below the lower layer plate, of the main shaft is fixedly connected with a rotating cam through a jackscrew, a limiting pin is arranged at a notch in one side of the rotating cam, and the other side of the rotating cam makes contact with switch handles of the two microswitches. According to the utility model, a more real operation damping feeling is provided for a driver.

Description

Technical Field

[0001] This utility model relates to the field of rotary switch structure technology, specifically a rotary switch structure for a backup static pressure source in a flight simulator. Background Technology

[0002] The backup static pressure source is an important backup device on an aircraft, used to provide static pressure data to flight instruments in the event of damage to or malfunction of the static pressure orifice, ensuring flight safety. The static pressure rotary switch is used to switch to the backup static pressure source when the main static pressure system fails, ensuring that the aircraft's flight parameters can continue to be measured accurately.

[0003] Currently, the existing backup static pressure source rotary switch has a poor tactile feel. Although it achieves signal triggering for two-position rotation, it cannot provide the driver with a more realistic sense of operating damping.

[0004] Therefore, a rotary switch structure for a backup static pressure source in a simulated aircraft is proposed to address the above problems. Utility Model Content

[0005] The purpose of this utility model is to provide a rotary switch structure for a backup static pressure source of a flight simulator, including a main shaft, an upper plate, and a lower plate. Circular holes are provided at corresponding positions in the middle of the upper and lower plates, and an oil-free bushing is embedded in each hole. The main shaft passes through the circular holes in the middle of the upper and lower plates from top to bottom. The top of the main shaft is connected to a rotating handle. A self-locking nut is threaded onto the main shaft below the upper plate. Below the self-locking nut, a flat washer, four disc springs, a friction plate, and a fluororubber ring are sequentially fitted onto the main shaft from top to bottom. The portion of the main shaft below the lower plate is fixedly connected to a rotating cam via a set screw. A limit pin is provided at a notch on one side of the rotating cam, and the other side of the rotating cam contacts the switch handles of two microswitches.

[0006] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0007] This invention reduces the complexity of the mechanical structure. By turning the self-locking nut, it moves up and down on the main shaft, thereby tightening or loosening the disc spring below, and adjusting the friction between the friction plate and the fluororubber ring to obtain the required operating damping feel. This provides the driver with a more realistic operating damping feel and has a better training effect.

[0008] This invention can simulate the backup static pressure source switch structure of various aircraft by changing the shape of the rotating handle. Attached Figure Description

[0009] Figure 1 This is a three-dimensional representation of the present invention. Figure 1 ;

[0010] Figure 2 This is a three-dimensional representation of the present invention. Figure 2 ;

[0011] Figure 3 This is a bottom view of the present invention;

[0012] Figure 4 This is a schematic diagram of the internal structure of this utility model.

[0013] The reference numerals and names in the figure are as follows:

[0014] 1. Rotating handle; 2. Spindle; 3. Oil-free bushing; 4. Upper plate; 5. Supporting hexagonal post; 6. Lower plate; 7. Connecting hexagonal post; 8. Self-locking nut; 9. Flat washer; 10. Disc spring; 11. Friction plate; 12. Fluoropolymer ring; 13. Limit pin; 14. Rotating cam; 15. Micro switch; 16. Circuit board. Detailed Implementation

[0015] 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.

[0016] As attached Figure 1-4 As shown, the present invention provides a rotary switch structure for a backup static pressure source of a simulated aircraft, including a main shaft 2, an upper plate 4, and a lower plate 6. Circular holes are provided at corresponding positions in the middle of the upper plate 4 and the lower plate 6, and an oil-free bushing 3 is embedded in each circular hole. The main shaft 2 passes through the circular holes in the middle of the upper plate 4 and the lower plate 6 sequentially from top to bottom. The top of the main shaft 2 is connected to a rotating handle 1. A self-locking nut 8 is threadedly connected to the threaded portion of the main shaft 2 below the upper plate 4. A flat washer 9, four disc springs 10, a friction plate 11, and a fluororubber ring 12 are sequentially fitted onto the main shaft 2 below the self-locking nut 8, from top to bottom. The portion of the main shaft 2 below the lower plate 6 is fixedly connected to a rotating cam 14 via a set screw. A limit pin 13 is provided at a notch on one side of the rotating cam 14, and the other side of the rotating cam 14 contacts the switch handles of two microswitches 15.

[0017] Specifically, the upper plate 4 has multiple threaded holes for fixing to the corresponding positions on the flight simulator.

[0018] Specifically, the upper plate 4 is connected to the lower plate 6 at its four lower corners by supporting hexagonal posts 5, and the lower plate 6 is provided with connecting hexagonal posts 7 at its four lower corners. The positions of the four supporting hexagonal posts 5 and the four connecting hexagonal posts 7 are arranged in a one-to-one correspondence.

[0019] Specifically, the friction plate 11 and the main shaft 2 are rotated and limited by the D-shaped hole opened on the friction plate 11.

[0020] Specifically, the lower part of the fluororubber ring 12 contacts the upper part of the lower plate 6.

[0021] Specifically, the rotating cam 14 and the main shaft 2 are rotated and limited by the D-shaped hole 2 opened on the rotating cam 14.

[0022] Specifically, a circuit board 16 is provided on one side below the lower plate 6. The circuit board 16 is electrically connected to the micro switch 15 and transmits the signals from the two micro switches 15 to the signal acquisition circuit of the flight simulator.

[0023] Working principle: The rotating handle 1 is rotated, which drives the rotating cam 14 at the tail end of the main shaft 2 to trigger the switch handles of the micro switches 15 at two positions to obtain the corresponding position signals. Since the limiting pin 13 under the lower plate 6 cooperates with the notch structure of the rotating cam 14, it can just limit the rotation angle of the rotating cam 14, thereby limiting the rotation angle of the rotating handle 1 fixed to the top of the main shaft 2, so that it can only rotate back and forth at an angle of 90 degrees. Tightening the self-locking nut 8 makes it move up and down on the main shaft 2, thereby pressing or releasing the disc spring 10 below, thereby adjusting the friction between the friction plate 11 and the fluororubber ring 12, and thus obtaining the required operating damping feel.

[0024] In the description of this utility model, it should be noted that the terms "upper," "lower," "inner," "outer," "front end," "rear end," "both ends," "one end," and "the other end," etc., 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 utility model 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 utility model. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. In the description of this utility model, it should be noted that unless otherwise explicitly specified and limited, the terms "installed," "equipped with," and "connected," etc., should be interpreted broadly. For example, "connection" 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 an indirect connection through an intermediate medium; it can be a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

Claims

1. A rotary switch structure for a backup static pressure source in a simulated aircraft, comprising a main shaft (2), an upper plate (4), and a lower plate (6), characterized in that: The upper plate (4) and the lower plate (6) are provided with round holes at corresponding positions in the middle. Each round hole is fitted with an oil-free bushing (3). The main shaft (2) passes through the round holes in the middle positions of the upper plate (4) and the lower plate (6) from top to bottom. The top of the main shaft (2) is connected to the rotating handle (1). The main shaft (2) is threaded with a self-locking nut (8) at the threaded part below the upper plate (4). A flat washer (9), four disc springs (10), a friction plate (11) and a fluororubber ring (12) are sequentially fitted on the main shaft (2) below the self-locking nut (8) from top to bottom. The part of the main shaft (2) below the lower plate (6) is fixedly connected to the rotating cam (14) by a set screw. A limit pin (13) is provided at the notch on one side of the rotating cam (14). The other side of the rotating cam (14) is in contact with the switch handles of two micro switches (15).

2. The rotary switch structure for a backup static pressure source in a flight simulator according to claim 1, characterized in that: The upper plate (4) is connected to the lower plate (6) at the four corners below by supporting hexagonal columns (5). The lower plate (6) is provided with connecting hexagonal columns (7) at the four corners below. The positions of the four supporting hexagonal columns (5) and the four connecting hexagonal columns (7) are arranged in a one-to-one correspondence.

3. The rotary switch structure for a backup static pressure source in a flight simulator according to claim 1, characterized in that: The friction plate (11) and the main shaft (2) are rotated and limited by the D-shaped hole opened on the friction plate (11).

4. The rotary switch structure for a backup static pressure source in a flight simulator according to claim 1, characterized in that: The fluororubber ring (12) is in contact with the lower layer plate (6) above.

5. The rotary switch structure for a backup static pressure source in a flight simulator according to claim 1, characterized in that: The rotating cam (14) and the main shaft (2) are rotated and limited by the D-shaped hole on the rotating cam (14).

6. The rotary switch structure for a backup static pressure source in a flight simulator according to claim 1, characterized in that: A circuit board (16) is provided on one side below the lower plate (6), and the circuit board (16) is electrically connected to the micro switch (15).

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