CN212411397U - Aircraft simulator control structure and linkage structure - Google Patents

Abstract

The application discloses aircraft simulator manipulation structure and linkage structure, this aircraft simulator manipulation structure includes: the device comprises a bracket, a total distance rod and an accelerator ring; the throttle ring is rotatably sleeved on the total distance rod, an output rocker arm is arranged on the throttle ring, the output rocker arm is hinged to an output connecting rod through a joint bearing, the output connecting rod is hinged to a supporting rod assembly through the joint bearing, the supporting rod assembly is hinged to the support through a rotating shaft, and the lower end of the supporting rod assembly is hinged to a throttle ring connecting rod, so that the rotary motion of the throttle ring is converted into the vertical motion of the throttle ring connecting rod; one end of the total distance rod is hinged to the support, and a total distance rod connecting rod is hinged to the total distance rod. The problem that in the prior art, the collective pitch rod and the throttle ring of the aircraft simulator are different in operation action, so that the operating parts of the collective pitch rod and the throttle ring are difficult to combine under the condition of no interference is solved.

Description

Aircraft simulator control structure and linkage structure

Technical Field

The application relates to the field of airplane simulators, in particular to an airplane simulator control structure and a linkage structure.

Background

The airplane simulator is developed synchronously with the development of simulation technology and aviation industry. The flight simulation device can simulate the flight of an aircraft in the air and the movement of the aircraft on the ground, can be used as a training and research tool, can effectively reduce the actually required flight time, saves fuel, reduces cost, is safer and more environment-friendly, and can also simulate operation such as strategic deployment and the like, so that the flight simulation device is more and more focused on the aviation industry, and the demand is continuously increased. In the simulated flight device or system, the operating component is the most important component, and all the simulated flight operations are completed through the operating component. The operational experience of the operational components directly affects the effectiveness of the flight training and may also affect the experience of the operator.

The operation parts of the aircraft simulator in the related art include a collective lever and a throttle ring, wherein the collective lever adopts a pull-up or push-down action during operation, and the throttle ring adopts a rotation action, so that the operation parts of the collective lever and the throttle ring are difficult to combine without interference due to different action directions.

Aiming at the problem that in the related art, the operating parts of a collective pitch lever and an accelerator ring of an aircraft simulator are difficult to combine under the condition of no interference due to different operation actions, an effective solution is not provided at present.

SUMMERY OF THE UTILITY MODEL

The main purpose of this application is to provide an aircraft simulator control structure to solve the problem that the collective pitch pole and throttle ring of aircraft simulator in the correlation technique are different because of the operation action, lead to the operational element of collective pitch pole and throttle ring to be difficult to combine under the condition that does not produce the interference.

In order to achieve the above object, the present application provides an aircraft simulator handling structure including: the device comprises a bracket, a total distance rod and an accelerator ring; the throttle ring is rotatably sleeved on the total distance rod, an output rocker arm is arranged on the throttle ring, the output rocker arm is hinged to an output connecting rod through a joint bearing, the output connecting rod is hinged to a supporting rod assembly through the joint bearing, the supporting rod assembly is hinged to the support through a rotating shaft, and the lower end of the supporting rod assembly is hinged to a throttle ring connecting rod, so that the rotary motion of the throttle ring is converted into the vertical motion of the throttle ring connecting rod; one end of the total distance rod is hinged to the support, and a total distance rod connecting rod is hinged to the total distance rod.

Furthermore, a mounting hole is formed in the total distance rod, the first end of the accelerator ring extends out of the total distance rod, the second end of the accelerator ring extends into the mounting hole, and the joint of the output rocker arm and the accelerator ring is located in the mounting hole, so that the output rocker arm can swing along with the accelerator ring.

Further, the branch subassembly include with the support passes through the sleeve that the pivot rotated to be connected and along the radial connecting plate that sets up of sleeve, output connecting rod lower extreme pass through joint bearing with the connecting plate upper end is articulated, the connecting plate lower extreme pass through joint bearing with throttle ring connecting rod is articulated.

Furthermore, the total distance rod is hinged with the bracket through a cross shaft, and an adjustable damper is arranged on the cross shaft, so that the damping of the total distance rod for pulling up and pressing down is adjustable; the end part of the throttle ring is provided with an adjustable damping ring so as to enable the rotating friction force of the throttle ring to be adjustable.

According to another aspect of the present application, there is provided an aircraft simulator maneuvering linkage structure comprising: the aircraft comprises two aircraft simulator control structures, a total distance rod linkage rocker arm, a total distance rod rotating shaft, an accelerator ring linkage rocker arm and an accelerator ring rotating shaft; the total distance rod linkage rocker arm is hinged with the lower end of the total distance rod connecting rod, and two ends of the total distance rod rotating shaft are respectively connected with the corresponding total distance rod linkage rocker arms; the throttle ring linkage rocker arm is hinged to the lower end of the throttle ring connecting rod, and two ends of the throttle ring rotating shaft are connected with the corresponding throttle ring linkage rocker arms respectively.

Furthermore, a total distance rod counter weight and an accelerator ring counter weight are respectively arranged on the total distance rod rotating shaft and the accelerator ring rotating shaft.

Further, still including setting up total apart from the pole pivot with the bearing frame at throttle ring pivot both ends, just the both ends of total apart from the pole pivot with the both ends of throttle ring pivot are equallyd divide and are do not connected with the bearing frame that corresponds through deep groove ball bearing and radial ball bearing.

Furthermore, the device also comprises at least one magnetic powder clutch, a torsion rocker arm, a connecting shaft and a connecting piece; the output end of the magnetic powder clutch is connected with the torsion rocker arm, the torsion rocker arm is hinged to the connecting shaft, the connecting shaft is hinged to the connecting piece, and the connecting piece is connected with the total distance rotating shaft.

Furthermore, the device also comprises a linear potentiometer, wherein the connecting piece is provided with a linkage shifting fork, the linkage shifting fork is sleeved on the total distance rotating shaft, the upper end of the linkage shifting fork is hinged with the connecting shaft, and the lower end of the linkage shifting fork is hinged with the input end of the linear potentiometer.

The adjustable damper is arranged on a transverse shaft of the total distance rod and the support, so that the damping of the total distance rod for pulling up and pressing down is adjustable.

In the embodiment of the application, the mode that the output rocker arm is matched with the output connecting rod is adopted, the throttle ring is rotatably sleeved on the total distance rod, the output rocker arm is arranged on the throttle ring, the output rocker arm is hinged with the output connecting rod through a joint bearing, the output connecting rod is hinged with a support rod assembly through a joint bearing, the support rod assembly is hinged with the support through a rotating shaft, the lower end of the support rod assembly is hinged with a throttle ring connecting rod, so that the rotating motion of the throttle ring is converted into the vertical motion of the throttle ring connecting rod, one end of the total distance rod is hinged on the support, the total distance rod connecting rod is hinged on the total distance rod, the purpose of not generating interference between the rotation of the throttle ring and the motion of the total distance rod is achieved, the technical effect of combining the throttle ring and the total distance rod on one operating component under the condition of not generating motion interference is realized, and the technical problem that the total distance rod, resulting in a problem that the collective lever and the operating parts of the throttle ring are difficult to be combined without interference.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this application, serve to provide a further understanding of the application and to enable other features, objects, and advantages of the application to be more apparent. The drawings and their description illustrate the embodiments of the invention and do not limit it. In the drawings:

FIG. 1 is a schematic structural diagram according to an embodiment of the present application;

FIG. 2 is a schematic cross-sectional view of FIG. 1;

FIG. 3 is an enlarged schematic view of a portion A of FIG. 2;

FIG. 4 is a linkage axis schematic view according to an embodiment of the present application;

FIG. 5 is another schematic isometric view of a linkage structure according to an embodiment of the present application;

the device comprises a support 1, a support rod assembly 2, a connecting plate 21, a sleeve 22, an adjustable damper 3, an output connecting rod 4, a mounting hole 5, an output rocker arm 6, a total distance rod 7, a total distance rod handle 8, a throttle ring 9, a total distance rod connecting rod 10, a throttle ring connecting rod 11, a total distance rod linkage rocker arm 12, a throttle ring linkage rocker arm 13, a rotating shaft 14, a transverse shaft 15, a total distance rod counterweight 16, a total distance rod rotating shaft 17, a throttle ring rotating shaft 18, a throttle ring counterweight 19, a magnetic powder clutch 20, a torsion rocker arm 23, a connecting shaft 24, a linear potentiometer 25, a linkage shifting fork 26 and a bearing seat 27.

Detailed Description

In order to make the technical solutions better understood by those skilled in the art, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only partial embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

It should be noted that the terms "first," "second," and the like in the description and claims of this application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It should be understood that the data so used may be interchanged under appropriate circumstances such that embodiments of the application described herein may be used.

In this application, the terms "upper", "lower", "inside", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings. These terms are used primarily to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to a particular orientation or to be constructed and operated in a particular orientation.

Moreover, some of the above terms may be used to indicate other meanings besides the orientation or positional relationship, for example, the term "on" may also be used to indicate some kind of attachment or connection relationship in some cases. The specific meaning of these terms in this application will be understood by those of ordinary skill in the art as appropriate.

Furthermore, the terms "disposed," "provided," "connected," "secured," and the like are to be construed broadly. For example, "connected" may be a fixed connection, a detachable connection, or a unitary construction; can be a mechanical connection, or an electrical connection; may be directly connected, or indirectly connected through intervening media, or may be in internal communication between two devices, elements or components. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.

In addition, the term "plurality" shall mean two as well as more than two.

It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.

As shown in fig. 1 to 5, an embodiment of the present application provides an aircraft simulator handling structure, including: the device comprises a bracket 1, a collective pitch rod 7 and an accelerator ring 9; the accelerator ring 9 is rotatably sleeved on the total distance rod 7, an output rocker arm 6 is arranged on the accelerator ring 9, the output rocker arm 6 is hinged with an output connecting rod 4 through a joint bearing, the output connecting rod 4 is hinged with a supporting rod component 2 through the joint bearing, the supporting rod component 2 is hinged with the support 1 through a rotating shaft 14, and the lower end of the supporting rod component 2 is hinged with an accelerator ring connecting rod 11, so that the rotating motion of the accelerator ring 9 is converted into the vertical motion of the accelerator ring connecting rod 11; one end of the total distance rod 7 is hinged on the bracket 1, and a total distance rod connecting rod 10 is hinged on the total distance rod 7.

In this embodiment, the support 1 is used for supporting the total distance rod 7 and the support rod assembly 2, since the total distance rod 7 and the support rod assembly 2 are both hinged on the support 1, in order to ensure the stress balance of the total distance rod 7 and the two ends of the support rod assembly 2, the support 1 can be composed of at least two vertical plates, the total distance rod 7 can be hinged with the two vertical plates through a cross shaft 15, the support rod assembly 2 is hinged with the two vertical plates through a rotating shaft 14, the total distance rod 7 can rotate around a hinged point with the support 1 to realize the actions of pulling up and pressing down, meanwhile, a total distance rod connecting rod 10 on the total distance rod 7 is driven to move in the vertical direction, the total distance rod connecting rod 10 is used for linking with the total distance rod 7 of another set of aircraft simulator operating structure, the throttle ring 9 is sleeved on the total distance rod 7 and is rotatably connected in a manner through a bearing, thereby ensuring the smooth rotation of the throttle ring 9, and the throttle ring 9 drives the output rocker arm 6 to rotate in the rotating, the output rocker arm 6 is hinged with the output connecting rod 4 through a joint bearing, so that the output connecting rod 4 can be driven to do upward or downward arc motion, the strut component 2 is hinged with the lower end of the output connecting rod 4 through the joint bearing, the strut component 2 can play a role in supporting the output connecting rod 4 and rotate around the rotating shaft 14 while the output connecting rod 4 does arc motion, and the strut component 2 is hinged with the throttle ring connecting rod 11, so that the throttle ring connecting rod 11 is driven to move in the vertical direction when the strut component 2 rotates around the rotating shaft 14, and the throttle ring connecting rod 11 is used for being linked with a throttle ring 9 of another group of airplane simulator control structures;

therefore, in the embodiment, the throttle ring 9 and the collective pitch lever 7 are combined together, and in the rotation process of the throttle ring 9, the structure related to the collective pitch lever 7 does not generate linkage, and in the process of pulling up or pressing down the collective pitch lever 7, due to the structure that the output end rocker arm is hinged with the output connecting rod 4 through the joint bearing, the collective pitch lever 7 only pulls the output connecting rod 4, the strut assembly 2 to rotate and the throttle ring connecting rod 11 to move, and does not drive the output rocker arm 6 to rotate, so that the throttle ring 9 is not driven to rotate in the collective pitch lever 7, that is, in the motion process of the throttle ring 9 and the collective pitch lever 7, the two do not generate interference with each other, and the problem that in the related art, due to different operation actions of the collective pitch lever 7 and the throttle ring 9 of the aircraft simulator, the operation parts of the collective pitch lever 7 and the throttle ring 9 are difficult to be combined under the condition of not generating.

In order to facilitate pulling of the collective pitch rod 7, a collective pitch rod handle 8 can be additionally arranged on the collective pitch rod 7.

As shown in fig. 1 to 5, the collective pitch rod 7 is provided with a mounting hole 5, a first end of the accelerator ring 9 extends out of the collective pitch rod 7, a second end extends to the mounting hole 5, and a joint of the output rocker 6 and the accelerator ring 9 is located in the mounting hole 5, so that the output rocker 6 can swing along with the accelerator ring 9.

Specifically, to further simplify the structure, the collective pitch rod 7 is hollow, and a mounting hole 5 is formed in the outer circumferential surface thereof, the mounting hole 5 is communicated with the inside of the collective pitch rod 7, the throttle ring 9 is sleeved in the collective pitch rod 7 through a bearing sleeve, one end of the throttle ring 9 extending out of the collective pitch rod 7 is used for rotating the throttle ring 9, the other end of the throttle ring extends to a position corresponding to the mounting hole 5, the output rocker arm 6 is fixed on the position corresponding to the throttle ring 9 and the mounting hole 5 through a screw, and the size of the output rocker arm 6 is smaller than that of the mounting hole 5, so that the output rocker arm 6 can be driven by the throttle ring 9 to move in the mounting hole 5 in the rotating process. The output end rocker arm is arranged along the radial direction of the accelerator ring 9, the included angle between the output connecting rod 4 and the motion plane of the output end rocker arm is larger than 10 degrees, and the output connecting rod 4 can be prevented from being blocked in the motion process through the included angle.

As shown in fig. 1 to 5, the strut assembly 2 includes a sleeve 22 rotatably connected to the bracket 1 via the rotating shaft 14 and a connecting plate 21 radially disposed along the sleeve 22, the lower end of the output link 4 is hinged to the upper end of the connecting plate 21 via a joint bearing, and the lower end of the connecting plate 21 is hinged to the throttle ring link 11 via a joint bearing.

Specifically, it should be noted that the sleeve 22 is connected to the rotating shaft 14 through a bearing, the rotating shaft 14 may be fixed to the bracket 1, the connecting plate 21 is located on the outer circumferential surface of the sleeve 22 and may be integrally formed with the sleeve 22, and the upper and lower ends of the connecting plate 21 are both provided with mounting lug seats and are hinged to the lower end of the output connecting rod 4 and the throttle ring connecting rod 11 through joint bearings, respectively, so as to support the movement process of the output connecting rod 4.

As shown in fig. 1 to 5, the collective pitch rod 7 is hinged with the bracket 1 through a transverse shaft 15, and the adjustable damper 3 is arranged on the transverse shaft 15, so that the damping of the upward pulling and the downward pressing of the collective pitch rod 7 is adjustable; the end of the throttle ring 9 is provided with an adjustable damping ring so that the rotational friction of the throttle ring 9 is adjustable.

Specifically, it should be noted that the collective pitch lever 7 is connected with the cross shaft 15 through a bearing, so that the collective pitch lever 7 can rotate on the support 1, the adjustable damper 3 is used for adjusting the damping force of the collective pitch lever 7 in the rotating process so as to simulate the change of the force of the collective pitch lever 7 in the flying process, and a damping ring is mounted at the rod end of the accelerator ring 9 to increase friction and adjust the friction so that the rotation of the accelerator ring 9 is closer to a real aircraft.

As shown in fig. 1 to 5, according to another aspect of the present application, there is provided an aircraft simulator manipulation linkage structure including: the aircraft simulator comprises two aircraft simulator operating structures, a total distance rod linkage rocker arm 12, a total distance rod rotating shaft 17, an accelerator ring linkage rocker arm 13 and an accelerator ring rotating shaft 18; wherein, the total distance rod linkage rocker arm 12 is hinged with the lower end of the total distance rod connecting rod 10, and two ends of the total distance rod rotating shaft 17 are respectively connected with the corresponding total distance rod linkage rocker arms 12; the accelerator ring linkage rocker arm 13 is hinged with the lower end of the accelerator ring connecting rod 11, and two ends of the accelerator ring rotating shaft 18 are respectively connected with the corresponding accelerator ring linkage rocker arms 13.

Specifically, it should be noted that the aircraft simulator includes a main pilot position and a secondary pilot position, and therefore at least two sets of aircraft simulator operating structures are required, and two sets of aircraft simulation operating structures need to be linked, and therefore in this embodiment, the linkage of the collective pitch levers 7 of the two aircraft simulator operating structures is realized by the collective pitch lever linkage rocker arm 12 and the collective pitch lever rotating shaft 17, and the linkage of the throttle ring 9 is realized by the throttle ring linkage rocker arm 13 and the throttle ring rotating shaft 18, specifically, when the collective pitch lever 7 of one aircraft simulator operating structure generates a vertical motion, the collective pitch lever linkage rocker arm 12 located at the lower end of the collective pitch lever 7 is driven to rotate, so as to drive the collective pitch lever rotating shaft 17 to rotate, and transmit a force to the collective pitch lever connecting rod 10 of the other aircraft simulator operating structure, and then drive the other collective pitch lever 7 to realize a synchronous motion, and the linkage of the throttle ring 9 has the same linkage principle as the collective pitch lever 7, and will not be described in detail herein.

As shown in fig. 1 to 5, a collective pitch lever spindle 17 and an accelerator ring spindle 18 are respectively provided with a collective pitch lever counterweight 16 and an accelerator ring counterweight 19, the total pitch lever 7 self weight can be overcome through the collective pitch lever counterweight 16, so that the total pitch lever 7 keeps smooth motion in the process of pulling up and pressing down when in use, the accelerator ring counterweight 19 on the accelerator ring spindle 18 can overcome the dead weight of the accelerator ring link 11, so that the hand feeling is closer to the operation of a real machine, a rotary potentiometer is adopted as an accelerator ring 9 potentiometer and is installed below the accelerator ring 9, the accelerator ring 9 rotates to drive the output shaft of the potentiometer to rotate, so as to collect a numerical value, and simultaneously, the collective pitch lever counterweight 7 and the accelerator ring 9 can be fixed at any position through the collective pitch lever counterweight 16 and the accelerator ring counterweight 19, and the positions of the collective pitch lever counterweight 16 and the accelerator ring counterweight 19 on corresponding axes can be adjusted.

As shown in fig. 1 to 5, the accelerator pedal further comprises bearing seats 27 disposed at two ends of the collective pitch lever rotating shaft 17 and the accelerator ring rotating shaft 18, and the two ends of the collective pitch lever rotating shaft 17 and the two ends of the accelerator ring rotating shaft 18 are respectively connected with the corresponding bearing seats 27 through deep groove ball bearings and radial ball bearings.

Specifically, it should be noted that, in the processing and installation process, the concentricity of the two ends of the collective pitch lever spindle 17 and the throttle ring spindle 18 has an error, so when the bearing seat 27 is installed, a deep groove ball bearing is selected at one end, a radial ball bearing is selected at the other end, the positions of the deep groove ball bearing corresponding to the collective pitch lever spindle 17 and the throttle ring spindle 18 are positioned, and the radial ball bearing overcomes the phenomena of clamping stagnation and unsmooth caused by the concentricity error.

As shown in fig. 1 to 5, the magnetic particle clutch further comprises at least one magnetic particle clutch 20, a torsional rocker 23, a connecting shaft 24 and a connecting piece; wherein, the output end of the magnetic powder clutch 20 is connected with a torsion rocker arm 23, the torsion rocker arm 23 is hinged with a connecting shaft 24, the connecting shaft 24 is hinged with a connecting piece, and the connecting piece is connected with the total distance rotating shaft 14.

Specifically, it should be noted that, in the actual flight process, the collective pitch post 7 can make the operating force sense of the collective pitch post 7 different because of the influence of environmental factors such as wind speed, height, etc., this problem can be solved by installing the magnetic powder clutch 20 on the collective pitch post pivot 17, change the torsion size of pivot 14 through changing the size of magnetic powder clutch 20 output shaft torsion, increase operator's experience sense, specifically, export different torsion through the magnetic powder clutch 20, the rethread torque rocking arm 23 and connecting shaft 24 transmit torsion to the collective pitch post 7 that corresponds on, because two collective pitch posts 7 adopt the mode of linkage, therefore magnetic powder clutch 20 adopts one can.

As shown in fig. 1 to 5, the linear potentiometer 7 further comprises a linear potentiometer 25, the connecting member is a linkage shifting fork 26, the linkage shifting fork 26 is sleeved on the collective pitch rotating shaft 14, the upper end of the linkage shifting fork 26 is hinged to the connecting shaft 24, the lower end of the linkage shifting fork is hinged to the input end of the linear potentiometer 25, the collective pitch rod 7 drives the linkage shifting fork 26 to synchronously rotate in the moving process, and simultaneously drives the input end of the linear potentiometer 25 connected to the lower end of the linkage shifting fork 26 to move, so that the moving stroke of the collective pitch rod 7 is obtained through the linear potentiometer 25, and the tail end of the linear potentiometer 25 is hinged to a fixed member due to the rotary movement of the linkage shifting fork 26.

The adjustable damping device is characterized by further comprising at least one adjustable damper 3 and a damping ring, wherein the damping ring is arranged at the end part of the accelerator ring 9, so that the rotating friction force of the accelerator ring 9 is adjustable, and the adjustable damper 3 is arranged on a transverse shaft 15, connected with the bracket 1, of the collective pitch rod 7, so that the damping of the collective pitch rod 7 in an upward pulling and downward pressing mode is adjustable.

The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims (10)

1. An aircraft simulator handling structure comprising: the device comprises a bracket, a total distance rod and an accelerator ring; wherein the content of the first and second substances,

the throttle ring is rotatably sleeved on the total distance rod, an output rocker arm is arranged on the throttle ring, the output rocker arm is hinged with an output connecting rod through a joint bearing, the output connecting rod is hinged with a supporting rod assembly through the joint bearing, the supporting rod assembly is hinged with the support through a rotating shaft, and the lower end of the supporting rod assembly is hinged with a throttle ring connecting rod, so that the rotary motion of the throttle ring is converted into the vertical motion of the throttle ring connecting rod;

one end of the total distance rod is hinged to the support, and a total distance rod connecting rod is hinged to the total distance rod.

2. The aircraft simulator handling structure of claim 1, wherein the collective pitch rod is provided with a mounting hole, the throttle ring has a first end extending out of the collective pitch rod and a second end extending into the mounting hole, and a connection between the output rocker arm and the throttle ring is located in the mounting hole, so that the output rocker arm can swing with the throttle ring.

3. The aircraft simulator handling structure of claim 2, wherein the strut assembly comprises a sleeve rotatably connected to the support via a rotating shaft and a connecting plate radially disposed along the sleeve, the lower end of the output link is hinged to the upper end of the connecting plate via a joint bearing, and the lower end of the connecting plate is hinged to the throttle ring link via a joint bearing.

4. An aircraft simulator handling structure according to any of claims 1 to 3, wherein the collective rod is articulated to the support by a transverse shaft, the transverse shaft being provided with an adjustable damper to allow adjustable damping of the collective rod pulling up and down;

the end part of the throttle ring is provided with an adjustable damping ring so as to enable the rotating friction force of the throttle ring to be adjustable.

5. An aircraft simulator maneuvering linkage structure, comprising: two aircraft simulator operating structures according to any one of claims 1 to 3, a collective lever link rocker, a collective lever pivot, a throttle ring link rocker and a throttle ring pivot; wherein the content of the first and second substances,

the total distance rod linkage rocker arm is hinged with the lower end of the total distance rod connecting rod, and two ends of the total distance rod rotating shaft are respectively connected with the corresponding total distance rod linkage rocker arms;

the throttle ring linkage rocker arm is hinged to the lower end of the throttle ring connecting rod, and two ends of the throttle ring rotating shaft are connected with the corresponding throttle ring linkage rocker arms respectively.

6. The aircraft simulator maneuvering linkage structure of claim 5, wherein a collective lever counterweight and a throttle ring counterweight are disposed on the collective lever shaft and the throttle ring shaft, respectively.

7. The aircraft simulator manipulation linkage structure of claim 5, further comprising bearing seats arranged at both ends of the collective pitch lever rotating shaft and the throttle ring rotating shaft, and both ends of the collective pitch lever rotating shaft and both ends of the throttle ring rotating shaft are respectively connected with the corresponding bearing seats through deep groove ball bearings and radial ball bearings.

8. The aircraft simulator maneuvering linkage structure of claim 7, further comprising at least one magnetic particle clutch, a torsional rocker arm, a connecting shaft, and a connecting piece; wherein the content of the first and second substances,

the output end of the magnetic powder clutch is connected with the torsion rocker arm, the torsion rocker arm is hinged to the connecting shaft, the connecting shaft is hinged to the connecting piece, and the connecting piece is connected with the total distance rotating shaft.

9. The aircraft simulator manipulation linkage structure according to claim 8, further comprising a linear potentiometer, wherein the connecting member is configured as a linkage fork, the linkage fork is sleeved on the collective pitch rotating shaft, the upper end of the linkage fork is hinged to the connecting shaft, and the lower end of the linkage fork is hinged to an input end of the linear potentiometer.

10. An aircraft simulator operating linkage according to any of claims 6 to 9, further comprising at least one adjustable damper and a damping ring, the damping ring being provided at an end of the throttle ring to make the rotational friction of the throttle ring adjustable, the adjustable damper being provided on a transverse shaft connecting the collective lever to the bracket to make the damping of the collective lever being pulled up and down adjustable.

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