Aircraft cursor control device and damping adjustment system and method thereof

Abstract

A cursor control device for an aircraft includes a base and an end cap. The base is provided with a damping control unit and a trackball. The base is also provided with a damping generating unit. The base also includes a damping response unit that is connected to the damping generating unit to obtain the desired cursor control damping. The present invention also relates to a damping adjustment system and method for the cursor control device, which includes a signal receiving unit, a damping calculation unit, and a damping control unit. The signal receiving unit receives and processes a preset damping signal, an aircraft motion signal, and an initial cursor control feedback signal. The damping calculation unit receives the signal processed by the signal receiving unit and calculates a damping instruction, and includes a preset damping calculation module, an automatic damping adjustment calculation module, and a damping calculation and confirmation module. The damping control unit receives the damping instruction signal output by the damping calculation confirmation module to control the damping value of the cursor control device. This system can adapt to the actual operating state of the aircraft and achieve accurate cursor control.

Description

Technical Field

[0001] The present invention relates to the field of aviation technology, in particular to the interaction of aircraft systems, specifically to a cursor control device for aircraft-borne interaction, and further specifically to a damping adjustment system and method for an aircraft cursor control device. Background Art

[0002] On many existing aircraft models, when pilots need to view certain parameter signals during flight, they use a cursor control device (CCD) to control the movement of the cursor on the cockpit display. Because misoperation caused by factors such as airflow disturbances during flight can significantly impact aircraft safety, existing solutions typically design CCD inputs with low movement sensitivity. This design has significant drawbacks. Firstly, moving the cursor over a large range is extremely inconvenient, time-consuming, and inefficient. Secondly, reducing sensitivity does not effectively reduce cursor control misinputs caused by factors such as airflow disturbances.

[0003] In addition, different pilots have different preferences for the sensitivity of the cursor control device, and a cursor control device that cannot adjust the sensitivity affects the comfort of human-computer interaction.

[0004] Existing document US10732774B1 proposes a solution to improve the sensitivity of a cursor control device, which is mainly used to solve the technical problem of signal changes caused by environmental factors and user-specific factors (such as finger size, skin moisture, pollutants, etc.) of capacitive touch screens.

[0005] Existing document US8902165B1 proposes a cursor control device using an integrated scroll ring, which solves the technical problem of providing an improved electromechanical solution for computer input devices. The solution adopts a mechanical structure and a gear structure to control the trackball.

[0006] Existing document CN208255837U proposes an aviation trackball mouse, which aims to solve the technical problem of fixing the mouse on an onboard device, that is, using it in a dark environment.

[0007] Existing document CN103777787A proposes a trackball automatic suppression device and method for an aircraft cursor control system. This prior art addresses the use of cursor controllers in harsh environments. It primarily prevents the cursor ball from moving by cutting off control of the cursor controller, thereby preventing misoperation. Summary of the Invention

[0008] In view of the above problems existing in the prior art, an object of the present invention is to provide an aircraft cursor control device, which can adapt to the actual operating state of the aircraft to achieve accurate control of the cursor.

[0009] To achieve the above-mentioned objectives, the present invention provides an aircraft cursor control device, comprising a base and an end cover, wherein the base is provided with a damping control unit and a trackball, and is characterized in that the base is also provided with a damping generating unit controlled by the damping control unit; and further comprising a damping response unit to connect and cooperate with the damping generating unit in the base to obtain the required cursor control damping.

[0010] Preferably, the damping generating unit comprises a magnetic member, and the magnetic member is arranged outside the trackball along the circumference of the trackball.

[0011] Preferably, the magnetic member includes a magnetic ring or a plurality of magnetic blocks.

[0012] Preferably, the damping generating unit further includes a plurality of connection holes for connecting to the damping response unit.

[0013] Preferably, the damping response unit includes a damping response member, a connecting member and a preset damping member, wherein the damping response unit is in a form corresponding to the damping generating unit.

[0014] Preferably, the connecting member includes a plurality of studs or pins so as to be movably connected to the connecting hole along the axial direction of the connecting hole.

[0015] Preferably, the preset damping member is sleeved on the connecting member or directly fixed on the damping response member.

[0016] Preferably, the preset damping member is a coil spring to generate a force in a direction opposite to the magnetic damping force generated by the damping generating unit, thereby achieving a dynamic balance of force during the damping adjustment process.

[0017] Preferably, the damping response member is made of metal materials such as iron, cobalt, and nickel.

[0018] Preferably, the portion of the damping response member opposite to the damping generating unit is made of metal materials such as iron, cobalt, and nickel, and the remaining portion is made of materials including but not limited to rubber and plastic damping plates, rubber and foam plastics, damping composite materials, and damping coatings.

[0019] Another object of the present invention is to provide a damping adjustment system for an aircraft cursor control device, which can provide accurate control of the cursor according to the actual operating state of the aircraft and / or the pilot's preference.

[0020] To achieve the above-mentioned object, the present invention provides a damping adjustment system for the aforementioned aircraft cursor control device, the system comprising a signal receiving unit, a damping calculation unit and a damping control unit; wherein,

[0021] The signal receiving unit is used to receive and process the preset damping signal, the aircraft's motion signal, the initial cursor control feedback signal, and the adjusted cursor control feedback signal;

[0022] The damping calculation unit is used to receive the signal processed by the signal receiving unit and calculate the damping instruction, and the damping calculation unit includes a preset damping calculation module, an automatic adjustment damping calculation module, and a damping calculation and confirmation module;

[0023] The damping control unit is configured to receive the damping command signal output by the damping calculation unit to control the damping value of the cursor control device of the aircraft;

[0024] In the damping calculation unit:

[0025] The preset damping calculation module is used to receive the processed preset damping signal and the initial cursor control feedback signal output from the signal receiving unit;

[0026] The automatic damping adjustment calculation module is used to receive the motion signal of the aircraft and calculate additional damping instructions;

[0027] The damping calculation and confirmation module is used to receive the damping instruction output by the preset damping adjustment calculation module and the additional damping instruction output by the automatic damping adjustment calculation module and perform superposition calculation on them, and output the damping instruction to the damping control unit after calculation; then receive the adjusted cursor control feedback signal from the damping control unit and compare and confirm it with the pre-stored cursor control feedback signal interval to determine whether the current damping instruction is reasonable, and output the confirmed damping instruction signal again.

[0028] Preferably, the signal receiving unit includes a signal acquisition module and a signal processing module; the signal acquisition module is used to collect the preset damping signal, the aircraft motion signal, the initial cursor control feedback signal and the adjusted cursor control feedback signal, and the signal processing module limits or filters the preset damping signal, the aircraft motion signal, the initial cursor control feedback signal and the adjusted cursor control feedback signal.

[0029] Preferably, the aircraft operation signal includes the aircraft's attitude, acceleration, angular acceleration and vibration signal, and the initial cursor control feedback signal includes a trackball movement signal and a cursor movement signal.

[0030] Preferably, the preset damping calculation module receives a preset damping signal corresponding to a preset damping value, wherein the preset damping signal includes a plurality of preset damping levels, and the set damping levels are a set of damping values, which are preset and stored in the preset damping calculation module.

[0031] Preferably, the preset damping calculation module receives a preset damping signal corresponding to a preset damping value, wherein the preset damping signal includes different damping values ​​corresponding to different cursor movement speed intervals, and there is a preset relationship between the preset speed interval and the damping value.

[0032] Preferably, the automatic damping adjustment calculation module receives the processed aircraft motion signal as a basis for adjusting parameters and calculates an additional damping value or a damping gain value.

[0033] Preferably, the damping calculation and confirmation module receives the additional damping value or damping gain value and calculates the final damping instruction; when the automatic adjustment damping calculation module calculates a damping value, the damping value calculated by the damping calculation and confirmation module is the sum of the preset damping value and the damping value calculated by the automatic adjustment; when the automatic adjustment damping calculation module calculates a damping gain value, the damping value calculated by the damping calculation and confirmation module is the product of the preset damping value and the damping gain value calculated by the automatic adjustment.

[0034] Yet another object of the present invention is to provide a damping adjustment method for an aircraft cursor control device, which can provide accurate control of the cursor according to the actual motion state of the aircraft and / or the pilot's preference.

[0035] To achieve the above-mentioned object, the present invention provides a method for adjusting the damping of an aircraft cursor control device using the aforementioned damping adjustment system, comprising the following steps:

[0036] receiving a preset damping instruction, an aircraft motion signal, an initial cursor control feedback signal, and an adjusted cursor control feedback signal;

[0037] Determining a default preset damping value according to the preset damping instruction or the initial cursor control feedback signal, and automatically adjusting the damping value by real-time calculation according to the aircraft motion signal;

[0038] Calculating a damping instruction based on the preset damping value and the automatically adjusted damping value, and sending the damping instruction to a damping control unit of an aircraft cursor control device;

[0039] The damping control unit receives the damping instruction and adjusts the damping of the cursor control device;

[0040] Determine whether the adjusted cursor control feedback signal after the damping adjustment meets the requirements. When it meets the requirements, continue to output the damping value calculated based on the preset damping value and the automatically adjusted damping value; if it does not meet the requirements, issue the previous damping instruction that meets the requirements.

[0041] Preferably, the previous damping instruction that meets the requirements includes the instruction outputted by the damping calculation and confirmation module last time. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] Figure 1 is a schematic diagram of a cursor control device (CCD) of the aircraft of the present invention;

[0043] Figure 2 yes Figure 1 A partial schematic diagram of the cursor control device of the present invention is shown;

[0044] Figure 3 yes Figure 1 A schematic diagram of a damping response unit of a cursor control device according to the present invention is shown;

[0045] Figure 4 yes Figure 1 A schematic diagram of another embodiment of a damping response unit of a cursor control device according to the present invention is shown;

[0046] Figure 5 is a schematic diagram of a damping adjustment system of a cursor control device of an aircraft of the present invention;

[0047] Figure 6 yes Figure 5 A schematic diagram of a signal receiving unit of the damping adjustment system shown;

[0048] Figure 7 yes Figure 5 A schematic diagram of a damping calculation unit of the damping adjustment system shown; and

[0049] Figure 8A and Figure 8B They are respectively flow charts of the damping adjustment method of the cursor control device of the aircraft of the present invention. DETAILED DESCRIPTION

[0050] The specific embodiments of the present invention will be described below. It should be noted that in the specific description of these embodiments, in order to provide a concise description, this specification cannot provide a detailed description of all the features of the actual embodiments. It should be understood that in the actual implementation of any embodiment, just as in the process of any engineering project or design project, in order to achieve the specific goals of the developer and to meet system-related or business-related restrictions, various specific decisions are often made, and this will also change from one embodiment to another. In addition, it can also be understood that although the efforts made in this development process may be complex and lengthy, for ordinary technicians in the field related to the content disclosed by the present invention, some changes in design, manufacturing or production based on the technical content disclosed in this disclosure are just conventional technical means and should not be understood as the content of this disclosure being insufficient.

[0051] Unless otherwise defined, the technical or scientific terms used in the claims and description shall have the ordinary meaning understood by persons of ordinary skill in the technical field to which the invention belongs. The words "one" or "an" and the like used in the description and claims of the patent application of the present invention do not indicate a quantity limitation, but rather indicate the existence of at least one. Words such as "include" or "comprise" mean that the elements or objects appearing before "include" or "comprises" cover the elements or objects listed after "include" or "comprises" and their equivalents, and do not exclude other elements or objects. Words such as "connect" or "connected" and the like are not limited to physical or mechanical connections, nor are they limited to direct or indirect connections.

[0052] The following embodiments are merely exemplary in nature and are not intended to limit the invention or the application and uses of the invention.

[0053] Figure 1 The cursor control device CCD100 of the aircraft of the present invention, as shown in the figure, includes a base 101 and an end cover 102, a damping control unit 103 is provided in the base 101, and a trackball 104 and a damping generating unit 105 are connected to the damping control unit 103; and also includes a damping response unit 106.

[0054] Specifically, Figure 2As shown, the damping generating unit 105 is arranged outside the trackball 104 along the circumference thereof. Specifically, it can be a magnetic coil or multiple magnetic blocks (not shown) arranged along the circumference of the trackball 104. The damping generating unit 105 is controlled by the damping control unit 103. It will be understood that the damping generating unit 105 can convert the current from the damping control unit 103 into magnetic force, that is, generate a corresponding magnetic force in the magnetic coil according to the magnitude and direction of the current, thereby generating the desired cursor control damping.

[0055] from Figure 2 It can also be seen that the damping generating unit 105 also includes a plurality of connection holes 1051 for connecting the damping response unit 106; it can be understood that if the damping generating unit is a plurality of magnetic blocks, these mounting holes 1051 can also be respectively provided on each magnetic block.

[0056] For example Figure 3 As shown in the figure, the damping response unit 106 of the present invention can be driven to move by the magnetic force generated by the damping generating unit 105. Specifically, the damping response unit 106 includes a damping response member 1061, a connecting member 1062, and a predetermined damping member 1063. As shown in the figure, the damping response unit 106 is also annular as a whole to correspond to the magnetic ring of the damping generating unit 105, or it can be a magnetic block (not shown) corresponding to the magnetic block. That is, the damping response member 1061 can include multiple blocks mounted on the damping response member body.

[0057] The connecting member 1062 includes a plurality of studs or pins to be movably connected to the connecting hole 1051 on the damping generating unit 105 along the axial direction thereof. Figure 3 As shown, it can be mounted on the connector 1062, or it can be mounted as shown. Figure 4 As shown, the connecting member 1062 is directly connected to the damping response member 1061 at a distance from the connecting member 1062 on the circumference of the damping response member 1061.

[0058] The preset damping member 1063 can be a coil spring as shown in the figure. When the connecting member 1062 is installed in the connecting hole 1051, the required spring force is preset. The spring force is opposite to the direction of the magnetic damping force generated by the damping generating unit 105, thereby achieving a dynamic balance of force during the damping adjustment process, that is, attracting or repelling the damping generating unit 105.

[0059] In the present invention, the damping response member (ring) 1061 is generally made of materials such as iron, cobalt, and nickel. For example, to reduce the weight of the entire damping response unit 106, the portion that cooperates with the damping generating unit 105 can be made of the metal material described above, while the remaining portion can be made of materials including but not limited to rubber and plastic damping plates, rubber and foam plastics, damping composite materials, and damping coatings.

[0060] In the installed state, the damping generating unit 105 receives the current output from the damping control unit 103 and generates a certain magnetic force. The damping response unit 106 moves longitudinally along the connecting hole 1051 of the damping generating unit 105 in response to the magnetic force, and reaches a force balance under the balance of the reaction force of the preset damping member 1063, thereby stably applying a force to the trackball 104. When the user operates the cursor device, the trackball 104 additionally moves in a controlled manner under the preset damping conditions to overcome the influence of changes in the complex flight environment, thereby making the operation more accurate.

[0061] For example Figure 5-7 As shown, the damping control unit 103 of the present invention further includes a damping adjustment system 200 for controlling the damping generating unit 105 to obtain the required damping output, thereby correspondingly obtaining the required amount of motion in the damping response unit 106, and exerting a controlled influence on the motion of the trackball 104 to adapt to the influence of changes in the complex flight environment.

[0062] like Figure 5 As shown, the damping adjustment system 200 includes a signal receiving unit 201 , a damping calculation unit 202 and a damping control unit 203 .

[0063] Specifically, Figure 6 As shown, the signal receiving unit 201 includes a signal acquisition module 2011 and a signal processing module 2012. The signal acquisition module 2011 collects unprocessed preset damping signals, aircraft motion signals, initial cursor control feedback signals, and adjusted cursor control feedback signals sent by other aircraft systems. The preset damping signals generally refer to manually preset damping command signals. The aircraft operation signals include but are not limited to aircraft attitude, velocity (acceleration), angular velocity (angular acceleration), and vibration signals. The cursor control feedback signals include but are not limited to cursor control input signals (such as trackball movement) and cursor movement signals. The signal processing module 2012 is used to process the various signals collected by the signal acquisition module 2011, such as signal limiting and filtering, and transmit the processed signals to the damping calculation unit 202 as input signals to the damping calculation unit 202, namely, transmit the processed damping adjustment command, aircraft motion signals, and initial cursor control feedback signals.

[0064] Figure 7 Schematic diagram of the damping calculation unit 202 is shown. The damping calculation unit includes: a preset damping calculation module 2021, an automatic damping adjustment calculation module 2022 and a damping calculation and confirmation module 2023; wherein:

[0065] The preset damping calculation module 2021 receives a preset damping signal corresponding to a preset damping value and uses the preset damping signal as the preset default damping value of the system. Specifically, the preset methods include the following two methods:

[0066] One is to set it by presetting several damping levels: the set damping level is a set of damping values, which are preset and stored in the preset damping calculation module 2021; that is, before using the damping adjustment system of the aircraft cursor control device, the user selects a damping value in the set of damping values ​​as the preset damping level.

[0067] The second method is to set the damping signal based on the initial current movement of the cursor control device. When the damping adjustment system of the aircraft cursor control device does not have a preset damping level, the user of the cursor control device determines the preset damping signal based on certain characteristics of the cursor control device. These characteristics include, for example, cursor movement speed, different cursor movement speed ranges corresponding to different damping values, and the relationship between the preset speed ranges and damping values. Before officially using the damping adjustment system, the user is required to use the cursor control device to complete a specific action, such as sliding from point A to point B along a certain trajectory. The preset damping value is determined based on certain characteristics of completing this specific action (such as cursor movement speed).

[0068] Automatic damping calculation module 2022 is configured to receive processed aircraft motion signals as a basis for adjusting parameters and calculate additional damping values ​​or damping gain values. These processed aircraft motion signals include, but are not limited to, aircraft attitude, velocity, acceleration, angular acceleration, and vibration signals. Automatic damping calculation module 2022 calculates the damping value or damping gain value in real time by receiving the processed aircraft motion signals. This calculates the damping value or damping gain value in real time to overcome adverse effects on cursor control during aircraft motion, thereby enabling precise control.

[0069] Preferably, the aforementioned damping value or damping gain value is adjusted in real time based on the aircraft's motion state. For example, in one embodiment, a corresponding damping correction table can be selected based on the vibration level at the aircraft seat. The damping correction table can include damping correction values ​​corresponding to different aircraft lateral accelerations and normal accelerations within the corresponding vibration range. Different vibration levels can correspond to different damping correction tables, and these damping correction tables are pre-determined through experiments at different lateral and normal accelerations using a predetermined vibration step size.

[0070] Table 1 below shows an example damping correction table according to an embodiment of the present application.

[0071] Table 1

[0072] Vibration value V <![CDATA[Lateral acceleration (Ay1)]]> <![CDATA[Lateral acceleration (Ay2)]]> …… <![CDATA[Lateral acceleration (Ay n )]]> <![CDATA[Normal acceleration (Az1)]]> <![CDATA[D 11 、K 11 ]]> <![CDATA[D 12 、K 12 ]]> … <![CDATA[D 1n 、K 1n ]]> <![CDATA[Normal acceleration (Az2)]]> <![CDATA[D 21 、K 21 ]]> <![CDATA[D 22 、K 22 ]]> … <![CDATA[D 2n 、K 2n ]]> …… … … … <![CDATA[Normal acceleration (Az m )]]> <![CDATA[D m1 、K m1 ]]> <![CDATA[D m2 、K m2 ]]> … <![CDATA[D mn 、K mn ]]>

[0073] It can be seen from Table 1 that when the vibration value at the aircraft seat is V, different normal accelerations Az i (where i = 1,…, m) and the lateral acceleration Ay i (where j = 1, ..., n) corresponds to the automatic damping adjustment value D ij and damping gain value K ij Table 1 gives m normal accelerations and n lateral accelerations, where m and n are positive integers greater than or equal to 1.

[0074] The damping calculation and confirmation module 2023 is responsible for checking and confirming the input damping signal and outputting the damping command signal after calculation. Specifically, the input damping signal comes from the damping values ​​output by the preset damping calculation module 2021 and the automatic adjustment damping calculation module 2022, and these damping values ​​are compared and confirmed with the adjusted cursor control feedback signal to ensure the correctness of the output damping command signal. The "confirmation" is: in the damping calculation and confirmation module 2023, the intervals of the cursor control feedback signal corresponding to different damping command signals are pre-specified, and whether the damping signal value is correct is determined by judging whether the received adjusted cursor control feedback signal is within the pre-specified interval. The "pre-specified intervals of the cursor control feedback signal corresponding to different damping command signals" are obtained based on pre-experiments or simulation calculations. The comparison process is as follows. Figure 8A shown.

[0075] Specifically, the damping calculation and confirmation module 2023 receives the damping value or damping gain value, calculates the final damping instruction, and sends it. For example, in one embodiment, if the automatic damping calculation module 2022 calculates a damping value, the damping value calculated by the damping calculation and confirmation module 2023 is the sum of the preset damping value and the automatic damping value. In another embodiment, if the automatic damping calculation module 2022 calculates a damping gain value, the damping value calculated by the damping calculation and confirmation module 2023 is the product of the preset damping value and the damping gain value.

[0076] After the cursor control feedback signal instructs the damping control unit 103 to perform damping adjustment according to the damping instruction signal, the user uses certain features of the cursor control device, such as the cursor movement speed, to determine whether the cursor movement speed under the current damping instruction is within the preset cursor movement speed range. If it is within the preset cursor movement speed range, a damping instruction calculated based on the damping value output by the preset damping calculation module 2021 and the automatic adjustment damping calculation module 2022 is issued; if it is not within the preset cursor movement speed range, a previous damping instruction that meets the requirements is issued, and the previous damping instruction that meets the requirements is the instruction output by the damping calculation and confirmation module last time or the instruction output by the preset damping calculation module. For example, this "confirmation" process is: "The step of determining whether the cursor movement speed is within the preset speed range" occurs after the damping instruction is calculated according to the current aircraft state, and the damping control unit adjusts the cursor movement speed according to the damping instruction signal and returns it to the damping calculation and confirmation module 2023 as the adjusted cursor control feedback signal, that is, first sending out the calculated damping instruction signal, then changing the damping according to the signal, and then feeding back the cursor movement speed after the damping change, and then comparing the fed-back cursor movement speed with the cursor movement speed signal corresponding to the calculated damping instruction.

[0077] However, it will be appreciated by those skilled in the art that when the user only wishes to adjust the damping value according to personal preference, the function of the automatic adjustment damping calculation module 2022 may be turned off, such as Figure 8B As shown, at this time, only the signal from the preset damping calculation module 2021 enters the damping calculation and confirmation module 2023, and only this signal is compared with the adjusted cursor control feedback signal.

[0078] Therefore, the present invention also relates to a method for adjusting the damping of an aircraft cursor control device using the damping adjustment system, comprising the following steps:

[0079] receiving a preset damping instruction, an aircraft motion signal, an initial cursor control feedback signal, and an adjusted cursor control feedback signal;

[0080] Determining a default preset damping value according to the preset damping instruction or the initial cursor control feedback signal, and automatically adjusting the damping value by real-time calculation according to the aircraft motion signal;

[0081] Calculating a damping instruction based on the preset damping value and the automatically adjusted damping value, and sending the damping instruction to a damping control unit of an aircraft cursor control device;

[0082] The damping control unit receives the damping instruction and adjusts the damping of the cursor control device;

[0083] Determine whether the adjusted cursor control feedback signal after the damping adjustment meets the requirements. When it meets the requirements, continue to output the damping value calculated based on the preset damping value and the automatically adjusted damping value; when it does not meet the requirements, output the previous damping instruction that meets the requirements as the damping instruction, wherein the previous damping instruction that meets the requirements is the instruction output by the damping calculation and confirmation module last time.

[0084] The following describes specific application examples of the present invention in conjunction with the device, adjustment system and method of the present invention:

[0085] First, a preset damping value: for example, the set damping level is a set of damping values, which are preset and stored in the preset damping calculation module 2021; that is, before using the damping adjustment system of the aircraft cursor control device, the user selects a damping value from the set of damping values ​​as the preset damping level. For another example, the setting can be made based on the initial current movement of the cursor control device. When the damping adjustment system of the aircraft cursor control device does not set a preset damping level, the user of the cursor control device uses certain characteristics of the cursor control device to determine the preset damping signal. These characteristics include, for example, the cursor movement speed, different cursor movement speed ranges corresponding to different damping values, and the relationship between the preset speed ranges and the damping values. Before officially using the damping adjustment system, the user needs to use the cursor control device to complete a specific action, such as sliding from point A to point B along a certain trajectory, and determine the preset damping value based on certain characteristics of completing this specific action (such as the cursor movement speed).

[0086] Next, the cursor damping command enters the signal acquisition unit of the signal receiving unit and, after processing, is sent to the damping calculation unit, where damping calculation is performed. A preset damping calculation module calculates a preset damping value. Meanwhile, during flight, if the aircraft encounters turbulent air, the signal acquisition unit of the signal receiving unit receives the aircraft's current motion signal, which is processed by the signal processing module and output. The automatic damping calculation module calculates the current required damping value / damping gain and adds it to the damping value set by the preset damping calculation module. The damping calculation module then superimposes this value and issues a damping command signal. The damping control unit converts the damping command signal into a corresponding electrical signal and sends it to the damping response unit of the damping control module. The magnetic module of the damping response unit generates a magnetic force that attracts the damping module to produce the preset damping effect. At this point, the system receives the adjusted cursor control feedback signal and compares it with the preset range of cursor control feedback signals corresponding to different damping command signals in the damping confirmation module. If the adjusted cursor control feedback signal falls within the range, the system continues to output the signal that meets the requirements. If it does not fall within the range, the system continues to output the previously satisfied signal or the preset damping signal.

[0087] Of course, if the pilot tends to set the cursor damping command according to personal preference, the automatic adjustment damping calculation module does not work or does not participate in the work of the damping calculation and confirmation module. At this time, the damping calculation and confirmation module outputs the preset damping value as the damping command.

[0088] After the damping calculation is confirmed and verified, a damping command signal is issued. The damping control unit converts the damping command signal into a corresponding electrical signal and sends it to the damping response unit. The magnetic module of the damping response unit generates magnetic force to attract the damping module to produce a preset damping effect.

[0089] The system and method of the present invention described above in combination with the embodiments include the following beneficial effects:

[0090] The ability to adjust the damping of the cursor control device to address inaccurate cursor movement due to external disturbances during flight;

[0091] The preset damping calculation module allows pilots to adjust the damping according to their own preferences, improving the pilot's comfort in manipulating the cursor;

[0092] The automatic damping calculation module can adjust the damping of the cursor control device in real time according to the aircraft's flight status to reduce the impact of external disturbances on the pilot's cursor control;

[0093] The damping response unit can achieve stepless damping adjustment and improve the reliability of the device through the combination of electrical signals and mechanical structures.

Claims

1. An aircraft cursor control device, comprising a base and an end cap, wherein the base is provided with a damping control unit and a trackball, and the base is further provided with a damping generating unit controlled by the damping control unit; and further comprising a damping response unit connected to and cooperating with the damping generating unit in the base to obtain a desired cursor control damping; characterized in that: The damping response unit includes a damping response member, a connecting member, and a preset damping member, wherein the damping response unit is in a form corresponding to the damping generating unit; the connecting member includes a plurality of studs or pins so as to be movably connected to the connecting hole along the axial direction of the connecting hole; the preset damping member is sleeved on the connecting member or directly fixed on the damping response member; The preset damping member is a coil spring to generate a force in a direction opposite to the magnetic damping force generated by the damping generating unit, thereby achieving a dynamic balance of force during the damping adjustment process.

2. The aircraft cursor control device according to claim 1, wherein: The damping generating unit includes a magnetic member, and the magnetic member is arranged outside the trackball along the circumference of the trackball.

3. The aircraft cursor control device according to claim 2, wherein: The magnetic member includes a magnetic ring or a plurality of magnetic blocks.

4. The aircraft cursor control device according to claim 1, wherein: The damping generating unit further includes a plurality of connection holes for connecting the damping response unit.

5. The aircraft cursor control device according to claim 1, wherein: The damping response component is made of metal materials such as iron, cobalt, and nickel.

6. The aircraft cursor control device according to claim 1, wherein: The portion of the damping response member opposite to the damping generating unit is made of metal materials such as iron, cobalt, and nickel, and the remaining portion is made of materials including but not limited to rubber and plastic damping plates, rubber and foam plastics, damping composite materials, and damping coatings.

7. The damping adjustment system of the aircraft cursor control device according to claim 1, comprising a signal receiving unit, a damping calculation unit and a damping control unit; wherein: The signal receiving unit is used to receive and process the preset damping signal, the aircraft's motion signal, the initial cursor control feedback signal, and the adjusted cursor control feedback signal; The damping calculation unit is used to receive the signal processed by the signal receiving unit and calculate the damping instruction, and the damping calculation unit includes a preset damping calculation module, an automatic adjustment damping calculation module, and a damping calculation and confirmation module; The damping control unit is configured to receive the damping command signal output by the damping calculation unit to control the damping value of the cursor control device of the aircraft; In the damping calculation unit: The preset damping calculation module is used to receive the processed preset damping signal and the initial cursor control feedback signal output from the signal receiving unit; The automatic damping adjustment calculation module is used to receive the motion signal of the aircraft and calculate additional damping instructions; The damping calculation and confirmation module is used to receive the damping instruction output by the preset damping adjustment calculation module and the additional damping instruction output by the automatic damping adjustment calculation module and perform superposition calculation on them, and output the damping instruction to the damping control unit after calculation; then receive the adjusted cursor control feedback signal from the damping control unit and compare and confirm it with the pre-stored cursor control feedback signal interval to determine whether the current damping instruction is reasonable, and output the confirmed damping instruction signal again.

8. The damping adjustment system for an aircraft cursor control device according to claim 7, wherein: The signal receiving unit includes a signal acquisition module and a signal processing module; the signal acquisition module is used to collect the preset damping signal, the aircraft motion signal, the initial cursor control feedback signal, and the adjusted cursor control feedback signal; the signal processing module limits or filters the preset damping signal, the aircraft motion signal, the initial cursor control feedback signal, and the adjusted cursor control feedback signal.

9. The damping adjustment system for an aircraft cursor control device according to claim 8, wherein: The aircraft operation signal includes the aircraft's attitude, acceleration, angular acceleration and vibration signal, and the initial cursor control feedback signal includes the trackball movement signal and the cursor movement signal.

10. The damping adjustment system for an aircraft cursor control device according to claim 7, wherein: The preset damping calculation module receives a preset damping signal corresponding to a preset damping value, wherein the preset damping signal includes a plurality of preset damping levels. The preset damping levels are a set of damping values, which are preset and stored in the preset damping calculation module.

11. The damping adjustment system for an aircraft cursor control device according to claim 7, wherein: The preset damping calculation module receives a preset damping signal corresponding to a preset damping value, wherein the preset damping signal includes different damping values ​​corresponding to different cursor movement speed intervals, and there is a preset relationship between the preset speed interval and the damping value.

12. The damping adjustment system for an aircraft cursor control device according to claim 7, wherein: The automatic damping adjustment calculation module receives the processed aircraft motion signal as a basis for adjusting parameters and calculates an additional damping value or a damping gain value.

13. The damping adjustment system for an aircraft cursor control device according to claim 12, wherein: The damping calculation and confirmation module receives the additional damping value or damping gain value and calculates a final damping instruction; when the damping value calculated by the automatic adjustment damping calculation module is a damping value, the damping value calculated by the damping calculation and confirmation module is the sum of the preset damping value and the damping value calculated by the automatic adjustment; When the damping gain value is calculated by the automatic adjustment damping calculation module, the damping value calculated by the damping calculation and confirmation module is the product of the preset damping value and the damping gain value calculated by the automatic adjustment.

14. A method for adjusting the damping of an aircraft cursor control device using the damping adjustment system of claim 7, comprising the following steps: receiving a preset damping instruction, an aircraft motion signal, an initial cursor control feedback signal, and an adjusted cursor control feedback signal; Determining a default preset damping value according to the preset damping instruction or the initial cursor control feedback signal, and automatically adjusting the damping value by real-time calculation according to the aircraft motion signal; Calculating a damping instruction based on the preset damping value and the automatically adjusted damping value, and sending the damping instruction to a damping control unit of an aircraft cursor control device; The damping control unit receives the damping instruction and adjusts the damping of the cursor control device; determining whether the adjusted cursor control feedback signal after the damping adjustment meets the requirements, and if so, continuing to output the damping value calculated according to the preset damping value and the automatically adjusted damping value; If it does not meet the requirements, issue the previous damping command that meets the requirements.

15. The method according to claim 14, characterized in that The previous damping instruction that meets the requirements includes the instruction outputted by the damping calculation and confirmation module last time.

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