Levelmeter for aircraft simulator

Abstract

The utility model relates to the technical field of aviation simulation, and provides a level gauge for an aircraft simulator. The transverse rolling mechanism comprises a first driving piece, a first gear transmission assembly, a first encoder and a transverse rolling dial, and the first encoder and the first driving piece are fixedly connected with the shell; the pitching mechanism comprises a pitching support, a second driving piece, a second gear transmission assembly, a second encoder and a pitching dial, the rolling dial, the second driving piece and the second encoder are fixedly connected with the pitching support, and the pitching dial is rotationally connected with the pitching support; the first driving part is connected with the pitching support and an input shaft of the first encoder through a first gear transmission assembly, and the second driving part is connected with the pitching dial and an input shaft of the second encoder through a second gear transmission assembly. The horizon surface reduces the cost of the aircraft simulator and improves the accuracy and stability of attitude display of the simulator.

Description

Technical Field

[0001] This utility model relates to the field of aviation simulation technology, and in particular to a horizon table for an aircraft simulator. Background Technology

[0002] In aircraft simulation training, the altitude display is a crucial flight instrument used to provide pilots with real-time feedback on the aircraft's attitude, including pitch and roll angles. Accurate attitude display is essential for pilots to perform simulated flight operations, train flight skills, and make judgments in various flight situations.

[0003] Because real aircraft horizon gauges with gyroscopes are expensive, some simulators use replicas of real aircraft horizon gauges. These replicas simulate and display the aircraft's pitch and roll angles based on the pilot's joystick rotation. However, their accuracy is limited, and they are prone to wear, jamming, and other problems, resulting in poor accuracy and stability in displaying the simulator's attitude. Utility Model Content

[0004] This invention provides a horizon gauge for an aircraft simulator, which solves the problem of poor accuracy and stability in displaying the attitude of the simulator using existing replica horizon gauges.

[0005] This utility model provides a horizon table for an aircraft simulator, comprising:

[0006] case;

[0007] The rolling mechanism includes a first drive component, a first gear transmission assembly, a first encoder, and a rolling scale, wherein the first encoder and the first drive component are fixedly connected to the housing;

[0008] The pitch mechanism includes a pitch support, a second drive component, a second gear transmission assembly, a second encoder, and a pitch dial. The roll dial, the second drive component, and the second encoder are fixedly connected to the pitch support, and the pitch dial is rotatably connected to the pitch support. The first drive component is connected to the input shafts of the pitch support and the first encoder respectively through the first gear transmission assembly, and the second drive component is connected to the input shafts of the pitch dial and the second encoder respectively through the second gear transmission assembly.

[0009] According to the horizon table for an aircraft simulator provided by this utility model, it also includes:

[0010] Conductive slip rings, comprising a stator and a rotor electrically connected to each other;

[0011] The first gear transmission assembly includes a first gear, a second gear, and a third gear. The first drive member is connected to the first gear. The first gear, the second gear, the third gear, and the input shaft of the first encoder are sequentially connected in a transmission manner. The second gear, the pitch support, and the rotor are coaxially fixedly connected. The stator is fixedly connected to the housing and passes through the second gear, the pitch support, and the rotor. The rotor is electrically connected to the second drive member and the second encoder.

[0012] According to the present invention, a horizon indicator for an aircraft simulator is provided, wherein the roll mechanism further includes: a rotating shaft and a sleeve, the sleeve being fixedly connected to the housing, the rotating shaft being rotatably inserted through the sleeve and rotatably sleeved on the stator, the second gear, the rotating shaft and the rotor being coaxially fixedly connected, and the second driving member being electrically connected to the rotor.

[0013] According to the present invention, a horizon gauge for an aircraft simulator is provided, wherein the second gear transmission assembly includes a fifth gear and a sixth gear, the second drive member is connected to the fifth gear, the sixth gear meshes with the fifth gear and is coaxially and fixedly connected to the input shaft of the second encoder, and the sixth gear is connected to the pitch scale and is used to drive the pitch scale to rotate relative to the pitch support.

[0014] According to the present invention, a horizon gauge for an aircraft simulator includes a pitch dial comprising a dial body and a connecting rod. The connecting rod is rotatably connected to the pitch support and fixedly connected to the dial body. The connecting rod is provided with a sliding groove. A lever is fixedly connected to a sixth gear, and the lever passes through the sliding groove. When the sixth gear rotates, the lever can slide along the sliding groove and drive the connecting rod to rotate relative to the pitch support.

[0015] According to the present invention, a horizon indicator for an aircraft simulator is provided. The housing includes a base structure, a head structure, and a case. The base structure and the head structure are respectively installed at both ends of the case and form an accommodating space. The roll mechanism and the pitch mechanism are housed within the accommodating space. The head structure is provided with a window, which is arranged opposite to the roll scale and the pitch scale.

[0016] According to the present invention, a ground plane for an aircraft simulator is provided, wherein the base structure is provided with a plurality of connecting columns; the rolling mechanism further includes: a fixing plate, the fixing plate being fixedly connected to the base structure through the plurality of connecting columns, and the second driving member and the second encoder being fixedly connected to the fixing plate.

[0017] According to the present invention, a horizon indicator for an aircraft simulator is provided, wherein an aircraft plug is installed on the base structure, and the first drive component, the second drive component, the first encoder, and the second encoder are electrically connected to the aircraft plug; a fault flag structure and / or a lighting lamp are installed on the head structure, and the fault flag structure and the lighting lamp are electrically connected to the aircraft plug.

[0018] According to the present invention, a horizon gauge for an aircraft simulator is provided, wherein a micro switch is installed on the base structure, and a toggle element is movably inserted on the gauge head structure, and the toggle element and the micro switch are detachably connected.

[0019] According to the present invention, a horizon gauge for an aircraft simulator is provided, wherein a scale and a calibration knob are installed on the gauge head structure, and the calibration knob is connected to the scale for calibrating the roll angle.

[0020] This utility model provides a horizon gauge for an aircraft simulator. The first drive component of the roll mechanism drives the pitch mechanism to perform roll motion via a first gear transmission assembly, simulating the roll angle. Simultaneously, a first encoder detects the rotation angle of the drive end of the first drive component. The second drive component of the pitch mechanism drives the pitch dial to perform pitch motion via a second gear transmission assembly, simulating the pitch angle. Simultaneously, a second encoder detects the rotation angle of the drive end of the second drive component. Using this horizon gauge in an aircraft simulator achieves its purpose of training pilots while reducing the cost of the aircraft simulator. Furthermore, the high-precision transmission of the gear transmission assembly and the real-time detection and feedback of the rotation angle of the drive end of the drive component by the encoder improve the accuracy and stability of the simulator's attitude display. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0022] Figure 1 This is an exploded view of the horizon surface for the aircraft simulator provided by this utility model.

[0023] Figure 2 This is a schematic diagram showing the connection between the roll mechanism and the pitch mechanism in the horizon table of the aircraft simulator provided by this utility model.

[0024] Figure 3 This is a schematic diagram of the roll mechanism structure in the horizon table of the aircraft simulator provided by this utility model.

[0025] Figure 4 This is a partial structural schematic diagram of the roll mechanism in the horizon table of the aircraft simulator provided by this utility model.

[0026] Figure 5 This is a schematic diagram of the pitch mechanism structure in the horizon table of the aircraft simulator provided by this utility model.

[0027] Figure 6 This is a schematic diagram of the base assembly of the horizon table for the aircraft simulator provided by this utility model.

[0028] Figure 7 This is a schematic diagram of the header component of the horizon table for the aircraft simulator provided by this utility model.

[0029] Figure label:

[0030] 1. Housing; 11. Case; 12. Base structure; 121. Connecting plug; 122. Micro switch; 123. Connecting post; 13. Head structure; 131. Window; 132. Mounting post; 133. Fault flag structure; 134. Illumination lamp; 135. Actuator; 1351. Pull rod; 1352. Paddle; 136. Scale; 137. Calibration knob; 2. Roll mechanism; 21. First drive element; 22. First gear transmission assembly; 221. First gear; 222. Second gear ; 223, Third gear; 224, Fourth gear; 23, First encoder; 24, Roll dial; 25, Rotating shaft; 26, Sleeve; 27, Fixing plate; 28, Bearing; 3, Pitch mechanism; 31, Pitch support; 32, Second drive component; 33, Second gear transmission assembly; 331, Fifth gear; 332, Sixth gear; 34, Second encoder; 35, Pitch dial; 351, Disc body; 352, Connecting rod; 3521, Slide groove; 36, Lever; 4, Stator. Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of this utility model clearer, the technical solutions of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model.

[0032] In the description of the embodiments of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "first"..."fourth" are numbered for the purpose of clearly identifying product components and do not represent any substantial difference. The terms "installed," "connected," and "linked" should be interpreted broadly; for example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of this utility model according to the specific circumstances. Furthermore, "multiple" means two or more. In the specification and claims, "and / or" indicates at least one of the connected objects, and the character " / " generally indicates that the preceding and following related objects are in an "or" relationship.

[0033] The following is combined Figures 1-7 This invention describes a horizon table for an aircraft simulator.

[0034] like Figure 1 As shown, the aircraft simulator horizon indicator provided in this embodiment of the present invention includes a housing 1, a roll mechanism 2, and a pitch mechanism 3. The roll mechanism 2 includes a first drive member 21, a first gear transmission assembly 22, a first encoder 23, and a roll scale 24. The first encoder 23 and the first drive member 21 are fixedly connected to the housing 1. The pitch mechanism 3 includes a pitch support 31, a second drive member 32, a second gear transmission assembly 33, a second encoder 34, and a pitch scale 35. The second drive member 32, the roll scale 24, and the second encoder 34 are fixedly connected to the pitch support 31, and the pitch scale 35 is rotatably connected to the pitch support 31. The first drive member 21 is connected to the input shafts of the pitch support 31 and the first encoder 23 respectively via the first gear transmission assembly 22, and the second drive member 32 is connected to the input shafts of the pitch scale 35 and the second encoder 34 respectively via the second gear transmission assembly 33.

[0035] Among them, see Figure 7 The aircraft simulator uses a horizon indicator with a scale 136 fixed relative to the housing 1. The scale 136 is correspondingly set with the roll dial 24 and the pitch dial 35. When the roll dial 24 rolls relative to the housing 1, the roll marking indicated by the scale 136 represents the roll angle of the aircraft simulator. When the pitch dial 35 pitches relative to the housing 1, the pitch dial 35 pitches relative to the roll dial 24, causing the horizontal line on the pitch dial 35 to misalign with the horizontal line on the roll dial 24 in the direction of pitch movement. The pitch angle of the aircraft simulator can be determined based on the misalignment distance.

[0036] Specifically, the fixed end of the first drive component 21 and the first encoder 23 are respectively fixedly connected to the housing 1, either directly or indirectly through other structural components. See [link / reference] Figure 2 The drive end of the first drive component 21 is connected to the pitch support 31 via the first gear transmission assembly 22, driving the pitch support 31 to rotate relative to the housing 1. This causes the entire pitch mechanism 3 to roll, and the pitch support 31 drives the roll scale 24 to roll, causing the scale 136 to deflect relative to the roll scale 24, thus simulating the lateral angle of the aircraft simulator. Simultaneously, the power of the first drive component 21 is also transmitted to the input end of the first encoder 23 via the first gear transmission assembly 22. The first encoder 23 detects the rotation angle of the drive end of the first drive component 21 and feeds it back to the system for comparison with the actual rotation angle of the pilot's control stick to confirm the accuracy of the roll angle simulation. If inaccurate, the control of the first drive component 21 can be adjusted in a timely manner to ensure the accuracy and stability of the angle simulation.

[0037] See Figure 2 The fixed end of the second drive unit 32 and the second encoder 34 are respectively fixedly connected to the pitch support 31. The drive end of the second drive unit 32 is connected to the pitch scale 35 and the input shaft of the second encoder 34 via the second gear transmission assembly 33, driving the pitch scale 35 to rotate relative to the pitch support 31, i.e., to perform pitch motion. Since the roll scale 24 is fixedly connected to the pitch support 31, the horizontal line on the pitch scale 35 and the horizontal line on the roll scale 24 are misaligned in the pitch motion direction, thus simulating the pitch angle of the aircraft simulator. Simultaneously, the power of the second drive unit 32 is also transmitted to the input end of the second encoder 34 via the second gear transmission assembly 33. The second encoder 34 detects the rotation angle of the drive end of the second drive unit 32 and feeds it back to the system for comparison with the actual rotation angle of the pilot's control stick to confirm the accuracy of the pitch angle simulation. If inaccurate, the control of the second drive unit 32 can be adjusted in time to ensure the accuracy and stability of the angle simulation.

[0038] Optionally, both the first driving component 21 and the second driving component 32 are motors. Of course, the first driving component 21 and the second driving component 32 can also be other possible rotary driving components, such as hydraulic or pneumatic driving components.

[0039] The horizon gauge for an aircraft simulator provided in this embodiment of the invention uses a first drive member 21 of the roll mechanism 2 to drive a pitch mechanism 3 to perform roll motion via a first gear transmission assembly 22, thereby simulating the roll angle. Simultaneously, a first encoder 23 detects the rotation angle of the drive end of the first drive member 21. Similarly, a second drive member 32 of the pitch mechanism 3 drives a pitch scale 35 to perform pitch motion via a second gear transmission assembly 33, thereby simulating the pitch angle. Simultaneously, a second encoder 34 detects the rotation angle of the drive end of the second drive member 32. Using this horizon gauge in an aircraft simulator achieves the purpose of training pilots while reducing the cost of the aircraft simulator. Furthermore, the high-precision transmission of the gear transmission assembly and the real-time detection and feedback of the rotation angle of the drive end of the drive member by the encoder improve the accuracy and stability of the simulator's attitude display.

[0040] The aircraft simulator horizon indicator provided in this embodiment of the invention also includes a conductive slip ring, which comprises a stator 4 and a rotor (not shown in the figure) electrically connected to each other. The first gear transmission assembly 22 includes a first gear 221, a second gear 222, and a third gear 223. A first drive member 21 is connected to the first gear 221, and the first gear 221, second gear 222, third gear 223, and the input shaft of the first encoder 23 are sequentially connected for transmission. The second gear 222, the pitch support 31, and the rotor are coaxially and fixedly connected. The stator 4 is fixedly connected to the housing 1, passes through the second gear 222, the pitch support 31, and the rotor, and is electrically connected to the second drive member 32 and the second encoder 34.

[0041] The power of the first driving member 21 is transmitted to the pitch support 31 through the first gear 221 and the second gear 222, so as to drive the pitch mechanism 3 to roll as a whole. The power of the first driving member 21 is also transmitted to the first encoder 23 through the first gear 221, the second gear 222 and the third gear 223, so as to detect the rotation angle of the first driving member 21.

[0042] Specifically, the pitch support 31 is fixed to one side of the second gear 222, and the rotor of the conductive slip ring is fixed to the side of the pitch support 31 away from the second gear 222. The three rotate coaxially. The stator is sequentially inserted through the second gear 222, the pitch support 31, and the rotor, and slides in contact with the rotor. The rotor is electrically connected to the second drive component 32 and the second encoder 34. This avoids the cable from getting tangled during the roll motion of the pitch mechanism 3.

[0043] Optionally, the roll mechanism 2 further includes a fourth gear 224, which is coaxially and fixedly connected to the second gear 222. The first gear 221 meshes with the second gear 222, and the fourth gear 224 meshes with the third gear 223. The transmission ratio of the first gear 221 and the second gear 222 is less than 1, which reduces speed and improves the control accuracy of the roll motion of the pitch support 31. The diameter of the fourth gear 224 is smaller than that of the second gear 222, which allows for a more compact structure of the first gear transmission assembly 22, facilitating the miniaturization design of the device.

[0044] like Figure 3 As shown, in some optional embodiments, the rolling mechanism 2 further includes a rotating shaft 25 and a sleeve 26. The sleeve 26 is fixedly connected to the housing 1, and the rotating shaft 25 is rotatably inserted through the sleeve 26 and rotatably sleeved on the stator 4 of the conductive slip ring. The second gear 222, the rotating shaft 25, and the rotor of the conductive slip ring are coaxially fixedly connected, and the second drive member 32 is electrically connected to the rotor.

[0045] Specifically, the rolling mechanism 2 further includes a fixed plate 27, which is fixedly connected to the housing 1. The first drive component 21, the first encoder 23, and the sleeve 26 are respectively fixedly mounted on the fixed plate 27. The first gear 221, the second gear 222, and the third gear 223 are respectively rotatably mounted on the fixed plate 27. The sleeve 26 and the second gear 222 are coaxially arranged. The rotating shaft 25 passes through the sleeve 26, the fixed plate 27, and the second gear 222 in sequence, and the rotating shaft 25 is rotatably connected to the sleeve 26 and the fixed plate 27, and is coaxially fixed with the second gear 222. Optionally, such as Figure 4 As shown, the first drive component 21 and the first encoder 23 are fixedly connected to the fixing plate 27 by bolts or screws, and the sleeve 26 is threadedly connected to the fixing plate 27. The rotating shaft 25 is rotatably connected to the sleeve 26 through two spaced-apart bearings 28.

[0046] The housing 1 is equipped with a flight plug 121, the stator 4 is inserted through the rotating shaft 25, one end of which is fixedly connected to the housing 1 and electrically connected to the flight plug 121, and the other end is electrically connected to the rotor on the pitch support 31.

[0047] like Figure 5 As shown, in some optional embodiments, the second gear transmission assembly 33 includes a fifth gear 331 and a sixth gear 332. The second drive member 32 is connected to the fifth gear 331, and the sixth gear 332 meshes with the fifth gear 331 and is coaxially fixedly connected to the input shaft of the second encoder 34. The sixth gear 332 is connected to the pitch dial 35 and is used to drive the pitch dial 35 to rotate relative to the pitch support 31.

[0048] The second drive unit 32 and the second encoder 34 are fixedly mounted on the pitch bracket 31 by screws or bolts. The fifth gear 331, the sixth gear 332, and the pitch dial 35 are rotatably mounted on the pitch bracket 31. The power of the second drive unit 32 is transmitted to the pitch dial 35 through the fifth gear 331 and the sixth gear 332 to drive the pitch dial 35 to rotate relative to the pitch bracket 31. At the same time, it is also transmitted to the second encoder 34 to detect the rotation angle of the second drive unit 32.

[0049] Specifically, see Figure 5 The pitch dial 35 includes a dial body 351 and a connecting rod 352. The connecting rod 352 is rotatably connected to the pitch support 31 and fixedly connected to the dial body 351. The connecting rod 352 is provided with a sliding groove 3521, and a lever 36 is fixedly connected to the sixth gear 332, with the lever 36 passing through the sliding groove 3521. When the sixth gear 332 rotates, the lever 36 can slide along the sliding groove 3521 and drive the connecting rod 352 to rotate relative to the pitch support 31.

[0050] Specifically, a connecting rod 352 is connected to each side of the disc 351. Both connecting rods 352 are rotatably connected to the pitch support 31, and one of the connecting rods 352 has a sliding groove 3521. One end of the connecting rod 352 is rotatably connected to the pitch support 31, and the other end is fixedly connected to the disc 351. The sliding groove 3521 is located between the two rotatable connection points and extends along the length of the connecting rod 352. A grooved wheel is coaxially fixed to the sixth gear 332, and a lever 36 is mounted on the grooved wheel. The sixth gear 332 drives the grooved wheel to rotate, and the lever 36 on the grooved wheel drives the connecting rod 352 to rotate while simultaneously moving along the length of the connecting rod 352 within the sliding groove 3521. Through the cooperation of the lever 36 and the sliding groove 3521, accurate control of the pitch angle of the pitch dial 35 is achieved.

[0051] Optionally, the sixth gear 332 is positioned relative to the fifth gear 331 near the rotation center of the connecting rod 352. It should be noted that the Geneva wheel can also be coaxially and fixedly connected to the fifth gear 331, with the fifth gear 331 positioned relative to the sixth gear 332 near the rotation center of the connecting rod 352.

[0052] See Figure 1 In some optional embodiments, the housing 1 includes a base structure 12, a dial head structure 13, and a case 11. The base structure 12 and the dial head structure 13 are respectively mounted at both ends of the case 11 and enclose an accommodating space. The roll mechanism 2 and the pitch mechanism 3 are housed within the accommodating space. The dial head structure 13 is provided with a window 131, which is disposed opposite to the roll dial 24 and the pitch dial 35.

[0053] Specifically, the watch case 11 is a cylindrical shell structure with openings at both ends. The base structure 12 and the watch head structure 13 are respectively fixedly installed at both ends of the cylindrical shell structure to form an accommodating space. The roll mechanism 2 and the pitch mechanism 3 are located within this accommodating space. The watch head structure 13 and the watch case 11 are respectively fixedly connected to the base structure 12 by screws to facilitate the assembly, disassembly and maintenance of the device.

[0054] Optionally, the watch head structure 13 has a plurality of mounting posts 132 protruding on the side near the base structure 12, which are connected to the base structure 12, and an accommodating space is formed between the plurality of mounting posts 132. The watch case 11 is surrounded on the outside of the plurality of mounting posts 132, and the plurality of mounting posts 132 form structural support for the watch case 11 on the inside of the watch case 11.

[0055] like Figure 6 As shown in the embodiment of this utility model, the base structure 12 is provided with multiple connecting posts 123. The rolling mechanism 2 also includes a fixing plate 27, which is fixedly connected to the base structure 12 via the multiple connecting posts 123. The second drive member 32 and the second encoder 34 are fixedly connected to the fixing plate 27. The first drive member 21 and the first encoder 23 are located within the space enclosed by the multiple connecting posts 123. The multiple connecting posts 123 are fixedly connected to the fixing plate 27 with screws to facilitate the assembly, disassembly, and maintenance of the rolling mechanism 2.

[0056] like Figure 6 As shown in this embodiment of the invention, a flight plug 121 is mounted on the base structure 12, and the first drive component 21, the second drive component 32, the first encoder 23, and the second encoder 34 are electrically connected to the flight plug 121. A fault flag structure 133 and / or a lighting lamp 134 are mounted on the meter structure 13, and the fault flag structure 133 and the lighting lamp 134 are electrically connected to the flight plug 121.

[0057] Specifically, the fault flag structure 133 includes a rotary motor and a warning flag. The rotary motor is electrically connected to the flight plug 121, and the warning flag is connected to the drive end of the rotary motor. When a fault needs to be simulated, the rotary motor drives the hidden warning flag to rotate to the window 131 for display. The illumination light 134 is used to illuminate the dials of the roll dial 24 and the pitch dial 35 to simulate night flight.

[0058] A socket is fixed on the base structure 12, and one end of the stator 4 is inserted into the socket. The socket is electrically connected to the connector 121. The first drive unit 21 and the first encoder 23 are electrically connected to the socket, and the second drive unit 32 and the second encoder 34 are connected to the socket through the stator 4.

[0059] In this embodiment of the utility model, see Figure 6 A microswitch 122 is mounted on the base structure 12. (See also...) Figure 7A toggle element 135 is movably inserted on the meter head structure 13, and the toggle element 135 can be detachably connected to the micro switch 122.

[0060] Specifically, the actuating element 135 includes a pull rod 1351 and a lever 1352, with the lever 1352 connected to one end of the pull rod 1351. The meter head structure 13 is provided with a guide groove, through which the pull rod 1351 movably passes. The guide groove provides guidance for the movement of the pull rod 1351, and the lever 1352 can be moved closer to or away from the micro switch 122 by pulling the pull rod 1351.

[0061] Optionally, the lever 1351 is connected to the meter head structure 13 via a reset element. For example, when the lever 1351 is pulled away from the meter head structure 13, the paddle 1352 touches the micro switch 122, realizing roll and pitch reset; after the lever 1351 is released, the lever 1351 is separated from the micro switch 122 under the action of the reset element.

[0062] In this embodiment of the utility model, see Figure 7 The instrument head structure 13 is equipped with a scale 136 and a calibration knob 137. The calibration knob 137 is connected to the scale 136 and is used to calibrate the roll angle. The scale 136 is located within the window 131 of the instrument head structure 13, and the aircraft's roll angle is observed through the scale on the roll dial 24 indicated by the scale 136. The calibration knob is rotatably mounted on the instrument head structure 13 and fixedly connected to the scale 136. The roll angle is calibrated by rotating the calibration knob.

[0063] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this utility model, and not to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this utility model.

Claims

1. A horizon indicator for an aircraft simulator, characterized in that, include: case; The rolling mechanism includes a first drive component, a first gear transmission assembly, a first encoder, and a rolling scale, wherein the first encoder and the first drive component are fixedly connected to the housing; The pitch mechanism includes a pitch support, a second drive component, a second gear transmission assembly, a second encoder, and a pitch dial. The roll dial, the second drive component, and the second encoder are fixedly connected to the pitch support, and the pitch dial is rotatably connected to the pitch support. The first drive component is connected to the input shafts of the pitch support and the first encoder respectively through the first gear transmission assembly, and the second drive component is connected to the input shafts of the pitch dial and the second encoder respectively through the second gear transmission assembly.

2. A horizon indicator for a flight simulator according to claim 1, wherein, Also includes: Conductive slip rings, comprising a stator and a rotor electrically connected to each other; The first gear transmission assembly includes a first gear, a second gear, and a third gear. The first drive member is connected to the first gear. The first gear, the second gear, the third gear, and the input shaft of the first encoder are sequentially connected in a transmission manner. The second gear, the pitch support, and the rotor are coaxially fixedly connected. The stator is fixedly connected to the housing and passes through the second gear, the pitch support, and the rotor. The rotor is electrically connected to the second drive member and the second encoder.

3. A horizon indicator for a flight simulator according to claim 2, wherein, The rolling mechanism further includes: a rotating shaft and a sleeve, the sleeve being fixedly connected to the housing, the rotating shaft being rotatably inserted through the sleeve and rotatably sleeved on the stator, the second gear, the rotating shaft and the rotor being coaxially fixedly connected, and the second driving member being electrically connected to the rotor.

4. The horizon for aircraft simulators according to claim 1, characterized in that, The second gear transmission assembly includes a fifth gear and a sixth gear. The second drive member is connected to the fifth gear. The sixth gear meshes with the fifth gear and is coaxially and fixedly connected to the input shaft of the second encoder. The sixth gear is connected to the pitch dial and is used to drive the pitch dial to rotate relative to the pitch support.

5. A horizon indicator for a flight simulator according to claim 4, wherein, The pitch dial includes a dial body and a connecting rod. The connecting rod is rotatably connected to the pitch support and fixedly connected to the dial body. The connecting rod is provided with a sliding groove. A lever is fixedly connected to the sixth gear and passes through the sliding groove. When the sixth gear rotates, the lever can slide along the sliding groove and drive the connecting rod to rotate relative to the pitch support.

6. The horizon for aircraft simulators according to claim 1, characterized in that, The housing includes a base structure, a head structure, and a case. The base structure and the head structure are respectively installed at both ends of the case and form an accommodating space. The roll mechanism and the pitch mechanism are housed within the accommodating space. The head structure has a window, which is positioned opposite to the roll dial and the pitch dial.

7. A horizon indicator for a flight simulator according to claim 6, wherein The base structure is provided with multiple connecting columns; the rolling mechanism further includes: a fixing plate, which is fixedly connected to the base structure through the multiple connecting columns, and the second drive component and the second encoder are fixedly connected to the fixing plate.

8. A horizon indicator for a flight simulator according to claim 6, wherein, An aircraft plug is mounted on the base structure, and the first drive unit, the second drive unit, the first encoder, and the second encoder are electrically connected to the aircraft plug, respectively; a fault flag structure and / or a lighting lamp are mounted on the meter structure, and the fault flag structure and the lighting lamp are electrically connected to the aircraft plug.

9. A horizon indicator for a flight simulator according to claim 6, wherein, A micro switch is installed on the base structure, and an actuating element is movably inserted through the meter head structure. The actuating element and the micro switch can be detachably connected.

10. The horizon marker for an aircraft simulator according to claim 6, characterized in that, The meter head structure is equipped with a scale and a calibration knob, which is connected to the scale and used to calibrate the roll angle.

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