Thrust control device and method with integrated folding wing control

Abstract

This invention relates to the field of cockpit integrated design and verification technology, and provides a thrust control device and method integrating folding wing control. The device includes a thrust handle, a thrust reverser unit, a limit unit, a limit switch, a folding wing control indicator, and a control system. The folding wing control indicator is mounted on the side fender and folds up or unfolds synchronously with the corresponding folding wing. The limit unit is mounted on the folding wing control indicator and limits the rotation angle of the thrust handle. The limit switch is mounted on the thrust handle and controls the unlocking and locking of the limit unit. This invention integrates the device into a thrust control system to control a flight device equipped with folding wings to complete the folding and unfolding of the wingtips. Simultaneously, when the wingtips are folded, it restricts the pilot's control over thrust, preventing loss of control of the aircraft due to the folding wingtips not unfolding or locking, thereby improving flight safety.

Description

Technical Field

[0001] This invention relates to the field of cockpit integrated design and verification technology, and in particular to a thrust control device and method for integrated folding wing control. Background Technology

[0002] To facilitate airport operations and reduce airline costs, Boeing incorporated foldable wingtips into the third-generation 777. Before takeoff, the wingtips are lowered and locked, with the folded and fixed sections forming a complete high-aspect-ratio wing that remains in this state from takeoff to ascent, cruise, and landing. After landing, during deceleration on the runway, the wingtips fold upwards once the speed falls below a certain threshold, facilitating airport operations. From there, all the way to the boarding bridge, the aircraft can be handled like a conventional aircraft with a standard wingspan of less than 65 meters.

[0003] For airworthiness authorities, type approval not only addresses issues like strength and lifespan during normal use, but also pays special attention to the reliability and malfunction of the folding mechanism. If the wings fail to open properly during takeoff or flight, or fold unexpectedly, the wingspan and wing area will be lower than design requirements, resulting in a loss of lift. If one side opens while the other does not, asymmetric lift and drag will occur, potentially leading to a flight accident.

[0004] There is currently no technical solution for coordinating and controlling folding wings and thrust. Summary of the Invention

[0005] The purpose of this invention is to overcome the shortcomings of the prior art and provide a thrust control device and method that integrates folding wing control. By integrating the folding wing control device into the thrust control device, if the wingtip is not in place or reliably locked before takeoff or during flight, the thrust is controlled to automatically ensure that takeoff cannot occur.

[0006] The present invention adopts the following technical solution:

[0007] On the one hand, the present invention provides a thrust control device integrating folding wing control, including a thrust handle, a thrust reverser unit, a limit unit, a limit switch, a folding wing control indicator, and a control system;

[0008] The thrust handle can rotate along a first positioning line to control the engine speed. The first positioning line is the spanwise direction of the aircraft wing.

[0009] The thrust reverser unit is mounted on the thrust handle and is used to turn the engine thrust reverser on or off.

[0010] The folding wing control indicator is located on the side guards on both sides of the thrust handle, and folds up or unfolds synchronously with the aircraft folding wing to display the folding or unfolding status of the aircraft folding wing.

[0011] The limiting unit is disposed on the folding wing control indicator and is used to limit the rotation angle of the thrust handle and limit the operating stroke of the thrust handle;

[0012] The limit switch is mounted on the thrust handle and is used to control the unlocking and locking of the limit unit;

[0013] The control system is connected to the thrust handle, the reverse thrust unit, the limit unit, the limit switch, and the folding wing control indicator signal, respectively.

[0014] In addition to any of the possible implementations described above, a further implementation is provided in which the folding wing control indicator is a sheet-like or thin block-like structure, connected to the outside of the side guard plate via a first pivot, and can be folded up or unfolded along the first pivot; when folded up, the folding wing control indicator is in close contact with the side guard plate;

[0015] The folding wing control indicator has a mounting slot, and the limiting unit is installed in the mounting slot; the side guard plate has a first opening corresponding to the limiting unit; when the folding wing control indicator is in the folded state, the limiting unit can enter the inside of the side guard plate through the first opening, limiting the thrust handle to rotate within a certain angle range.

[0016] In addition to any of the possible implementations described above, a further implementation is provided in which the limiting unit includes a lever with a second rotating shaft disposed within the mounting groove; the initial position of the lever is within the mounting groove, at which time the limiting unit is in an unlocked state; when the lever rotates 90° from its initial position along the second rotating shaft, the lever passes through the first opening and enters the inner side of the side guard plate, limiting the travel range of the thrust handle.

[0017] In addition to any of the possible implementations described above, a further implementation is provided in which the device further includes a first motor and a second motor; the first motor drives the folding wing control indicator to rotate around a first rotating axis, and the second motor drives the toggle block to rotate around a second rotating axis; both the first motor and the second motor are signal-connected to the control system.

[0018] In addition to any of the possible implementations described above, another implementation is provided in which the limit switch is equipped with status indicator lights to indicate the locking and unlocking of the limit unit, and the unfolding and locking of the folding wing.

[0019] In addition to any of the possible implementations described above, a further implementation is provided in which a trigger switch is provided on the limiting unit and a corresponding second opening is provided on the side guard plate. When the limiting unit is folded up, the trigger switch passes through the second opening and enters the inner side of the side guard plate. When the push handle passes through the second opening, the trigger switch is triggered.

[0020] On the other hand, the present invention also provides a thrust control method with integrated folding wing control, using the above-mentioned thrust control device with integrated folding wing control, the method including locking the limit unit and unlocking the limit unit;

[0021] The locking of the limiting unit includes:

[0022] S1. Operate the limit switch, give a locking command and transmit it to the control system. The control system controls the folding wing to fold up. The corresponding folding wing control indicator folds up synchronously around the first rotating shaft under the drive of the first motor. The folding wing control indicator is in close contact with the side guard plate.

[0023] S2. The control system determines whether the thrust handle is in the slow position. If not, it controls the thrust handle to return to the slow position.

[0024] S3. The limiting unit located on the folding wing control indicator rotates around the second rotating shaft under the drive of the second motor. The toggle block of the limiting unit rotates and enters the inner side of the side guard plate through the first opening, limiting the thrust handle to rotate within the set angle range. At this time, the thrust handle only has a partial stroke.

[0025] The unlocking of the limiting unit includes:

[0026] X1. Operate the limit switch, give an unlock command and transmit it to the control system. The control system controls the limit unit's toggle block to rotate around the second shaft under the drive of the second motor, and the toggle block is retracted into the mounting slot.

[0027] X2. The control system controls the unfolding of the folding wings. The corresponding folding wing control indicator rotates synchronously around the first axis under the drive of the first motor, and the thrust handle returns to its full stroke.

[0028] In addition to any of the possible implementations described above, a further implementation is provided, wherein the method is used for high-speed ground taxiing protection and deactivation of high-speed ground taxiing protection during aircraft ground taxiing.

[0029] The ground skidding high-speed protection specifically includes:

[0030] When the aircraft engine is started, the folding wings are folded up, the limit unit is locked, and the limit switch is in the locked position.

[0031] When the aircraft's ground speed is lower than the speed limit, the aircraft taxis normally, and the limit unit restricts the rotation angle of the thrust handle to ensure that the aircraft's ground speed is lower than the speed limit.

[0032] When the aircraft's ground speed exceeds the speed limit, if the limit unit is in a locked state, the status of the limit unit is transmitted to the control system, and the control system drives the thrust handle back to the slow position.

[0033] The ground taxiing high-speed protection is released as follows:

[0034] Operate the limit switch and send a limit release command; the limit unit will unlock under the drive of the control system.

[0035] The thrust handle limit is released, the thrust handle returns to its full travel, and the aircraft ground taxiing speed limit is released.

[0036] In addition to any of the possible implementations described above, a further implementation is provided, wherein the method is used for the coordinated control of engine thrust and folding wings, including manual control and automatic control;

[0037] The manual control specifically refers to:

[0038] When the aircraft enters the runway to prepare for takeoff, the ground taxiing high-speed protection is released after the operation is completed.

[0039] By operating the limit switch, the control system controls the unfolding of the folding wings, and the corresponding folding wing control indicator unfolds synchronously.

[0040] When the folding wings on both sides are deployed, the position lockers on the folding wings lock, and a feedback signal is sent to the control system. The limit switches are released from their limit states, and the aircraft enters the takeoff procedure.

[0041] The automatic control specifically refers to:

[0042] When the aircraft enters the runway to prepare for takeoff, the ground taxiing high-speed protection is released after the operation is completed.

[0043] Push the thrust handle to the TOGA position. During the movement of the thrust handle, the trigger switch on the limit unit is activated. The trigger switch sends a feedback signal to the control system, which controls the folding wings to unfold. The corresponding folding wing control indicator unfolds synchronously. At the same time, after a thrust control delay, the wheel brake command is triggered, driving the aircraft's main wheels to brake.

[0044] When the folding wings on both sides are fully deployed, the position locks on the folding wings lock, and a feedback signal is sent to the control system, the limit switches are released from the limit state; the wheel brake command is released, and the active brake is released.

[0045] After the active braking is released for a certain period of time, the thrust control command is triggered, and the aircraft takeoff procedure is executed.

[0046] In addition to any of the possible implementations described above, another implementation is provided in which, when the folding wing actuation exhibits bilateral asymmetry, unilateral folding, failure, or jamming, the folding wing control indicators on both sides respectively indicate that the folding wing is driven to fold up or remain in the jammed position.

[0047] Simultaneously, a command is issued to drive the thrust handle back to the slow position; and to drive the limit switch and limit unit back to the locked state.

[0048] When the aircraft is in the air, the folding wing control indicator is locked, cutting off all control commands, and the limit switch is in the unfolded and locked state of the folding wings.

[0049] The beneficial effects of this invention are as follows: the device is integrated into the thrust control device to control the folding and unfolding of the wing tips of an aircraft equipped with folding wings; at the same time, when the wing tips are in the folded state, the pilot's control over thrust is restricted, avoiding loss of control of the aircraft due to the folding wing tips not unfolding or locking, thereby improving flight safety. Attached Figure Description

[0050] Figure 1 The diagram shown is a structural schematic of a thrust control device (folding wing control indicator in deployed state) integrating folding wing control according to an embodiment of the present invention.

[0051] Figure 2 The diagram shown is a schematic of a thrust control device integrating folding wing control in an embodiment (the folding wing control indicator is folded up and the limit unit is in a locked state).

[0052] Figure 3 The diagram shown is a schematic representation of a thrust control device integrating folding wing control in an embodiment (the folding wing control indicator is folded up and the limit unit is in the unfolded state).

[0053] Figure 4 The diagram shown is a schematic representation of the unfolded state of the folding wing indicator in the embodiment.

[0054] Figure 5 The diagram shown is a schematic representation of the process for ground taxiing high-speed protection and ground taxiing high-speed protection deactivation in the embodiment.

[0055] Figure 6 The diagram shown is a schematic of the manual control deployment process in the embodiment.

[0056] Figure 7 The diagram shown is a schematic of the automatic folding-up process during landing in an embodiment.

[0057] In the diagram: 1-Thrust handle; 2-Reverse thrust unit; 3-Limit unit; 4-Limit switch; 5-Folding wing control indicator; 6-Trigger switch; 7-Side guard plate; 8-First opening; 9-Second opening; 10-Mounting slot; 11-Pulley. Detailed Implementation

[0058] The specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the technical features or combinations of technical features described in the following embodiments should not be considered in isolation, but can be combined with each other to achieve better technical effects.

[0059] like Figures 1-4 As shown, an embodiment of the present invention provides a thrust control device integrating folding wing control, including a thrust handle 1, a reverse thrust unit 2, a limit unit 3, a limit switch 4, a folding wing control indicator 5, and a control system.

[0060] The thrust handle 1 can rotate along a first positioning line to control the engine speed. The first positioning line is the spanwise direction of the aircraft wing.

[0061] The thrust reverser unit 2 is mounted on the thrust handle 1 and is used to turn the engine thrust reverser on or off.

[0062] The folding wing control indicator 5 is installed on the side guard plates 7 located on both sides of the thrust handle 1, and folds up or unfolds synchronously with the aircraft folding wing to display the folding or unfolding status of the aircraft folding wing.

[0063] The limiting unit 3 is disposed on the folding wing control indicator 5 and is used to limit the rotation angle of the thrust handle 1 and limit the operating stroke of the thrust handle 1.

[0064] The limit switch 4 is mounted on the push handle 1 and is used to control the unlocking and locking of the limit unit 3.

[0065] The control system is connected to the thrust handle 1, the reverse thrust unit 2, the limit unit 3, the limit switch 4, and the folding wing control indicator 5 respectively.

[0066] The folding wing control indicator 5, the limiting unit 3, the toggle block 11, and the trigger switch 6 can all be implemented in various forms. The following are only preferred embodiments and are not intended to limit the scope of protection of this invention.

[0067] In one specific embodiment, such as Figure 1 As shown, the folding wing control indicator 5 is a sheet-like or thin block structure, connected to the outside of the side guard plate 7 via a first pivot, and can be folded up or unfolded along the first pivot; when folded up, the folding wing control indicator 5 is in close contact with the side guard plate 7, such as... Figure 2 As shown;

[0068] The folding wing control indicator 5 has a mounting groove 10, and the limiting unit 3 is disposed in the mounting groove 10; the side guard plate 7 has a first opening 8 corresponding to the limiting unit 3, such as... Figure 4 As shown; when the folding wing control indicator 5 is in the folded state, the limiting unit 3 can enter the inner side of the side guard plate 7 through the first opening 8, limiting the thrust handle 1 to rotate within a certain angle range.

[0069] In one specific embodiment, the limiting unit 3 includes a lever 11 with a second rotating shaft, the second rotating shaft being disposed within the mounting groove 10; the initial position of the lever 11 is within the mounting groove 10, at which time the limiting unit 3 is in an unlocked state; when the lever 11 rotates 90° from its initial position along the second rotating shaft, the lever 11 passes through the first opening 8 and enters the inner side of the side guard plate 7, limiting the travel range of the thrust handle 1, such as... Figure 2 , Figure 4 As shown.

[0070] In one specific embodiment, a first motor drives the folding wing control indicator 5 to rotate around a first rotating axis, and a second motor drives the toggle block 11 to rotate around a second rotating axis. Both the first motor and the second motor are signal-connected to the control system.

[0071] In one specific embodiment, the limit switch 4 is equipped with status indicator lights to indicate the locking and unlocking of the limit unit 3, and the unfolding and locking of the folding wing.

[0072] Preferably, a red indicator light indicates that the device is locked, an off light indicates that it is unlocked, and a green light indicates that the folding wings are deployed and locked.

[0073] In one specific embodiment, such as Figure 4 As shown, a trigger switch 6 is provided on the limiting unit 3, and a corresponding second opening 9 is provided on the side guard plate 7. When the limiting unit 3 is folded up, the trigger switch 6 passes through the second opening 9 and enters the inner side of the side guard plate 7. When the push handle 1 passes through the second opening 9, it triggers the trigger switch 6.

[0074] On the other hand, the present invention also provides a thrust control method with integrated folding wing control, using the above-mentioned thrust control device with integrated folding wing control, the method including locking the limiting unit 3 and unlocking the limiting unit 3;

[0075] The locking mechanism of the limiting unit 3 includes:

[0076] S1. Operate the limit switch 4, give a locking command and transmit it to the control system. The control system controls the folding wing to fold up. The corresponding folding wing control indicator 5 folds up synchronously around the first rotating shaft under the drive of the first motor. The folding wing control indicator 5 is in close contact with the side guard plate 7.

[0077] S2. The control system determines whether the thrust handle 1 is in the slow position. If not, it controls the thrust handle 1 to return to the slow position.

[0078] S3. The limiting unit 3 located on the folding wing control indicator 5 rotates around the second rotating shaft under the drive of the second motor. The toggle block 11 of the limiting unit 3 rotates and enters the inner side of the side guard plate 7 through the first opening 8, limiting the thrust handle 1 to rotate within the set angle range and not allowing it to exceed the degree limit. At this time, the thrust handle 1 only has a partial stroke.

[0079] The unlocking of the limiting unit 3 includes:

[0080] X1. Operate the limit switch 4, give an unlocking command and transmit it to the control system. The control system controls the toggle block 11 of the limit unit 3 to rotate around the second shaft under the drive of the second motor. The toggle block is retracted into the mounting slot 10.

[0081] X2. The control system controls the unfolding of the folding wings. The corresponding folding wing control indicator 5 is driven by the first motor to rotate synchronously around the first rotating shaft and unfold. The thrust handle 1 returns to its full stroke.

[0082] In one specific embodiment, such as Figure 5 As shown, the method is used for high-speed ground taxiing protection and deactivation during aircraft ground taxiing.

[0083] The ground skidding high-speed protection specifically includes:

[0084] When the aircraft engine is started, the folding wings are folded up, the limit unit 3 is locked, and the limit switch 4 is in the locked position (the red light of limit switch 4 is on).

[0085] When the aircraft's ground speed is lower than the speed limit (e.g., the speed limit is 50 Kn), the aircraft taxis normally, and the limit unit 3 limits the rotation angle of the thrust handle 1 to ensure that the aircraft's ground speed is lower than the speed limit.

[0086] When the aircraft's ground speed exceeds the speed limit, if the limit unit 3 is in a locked state, the state of the limit unit 3 is transmitted to the control system, and the control system drives the thrust handle 1 back to the slow position.

[0087] The ground taxiing high-speed protection is released as follows:

[0088] Operate limit switch 4 (e.g., click) to send a limit release command, and limit unit 3 will unlock under the drive of the control system (limit switch 4 light goes out);

[0089] The thrust handle 1 limit is released, the thrust handle 1 returns to its full travel, and the aircraft ground taxiing speed limit is released.

[0090] In one specific embodiment, the method is used for the coordinated control of engine thrust and folding wings, including manual control and automatic control;

[0091] like Figure 6 As shown, the manual control specifically includes:

[0092] When the aircraft enters the runway to prepare for takeoff, the ground taxiing high-speed protection is released after the operation is completed.

[0093] By operating the limit switch 4 (e.g., by double-clicking), the control system controls the folding wings to unfold, and the corresponding folding wing control indicator 5 unfolds synchronously.

[0094] When the folding wings on both sides are deployed, the position lockers on the folding wings lock and send a feedback signal to the control system. Limit switch 4 is released from the limit state (the green light of limit switch 4 is on), and the aircraft enters the takeoff procedure.

[0095] The automatic control specifically refers to:

[0096] When the aircraft enters the runway to prepare for takeoff, the ground taxiing high-speed protection is released after the operation is completed.

[0097] Push the thrust handle 1 to the TOGA position. During the movement of the thrust handle 1, the trigger switch 6 on the limit unit 3 is activated. The trigger switch 6 sends a feedback signal to the control system, which controls the folding wings to unfold. The corresponding folding wing control indicator 5 unfolds synchronously. At the same time, the thrust control delay triggers the wheel brake command, driving the aircraft main wheel brake.

[0098] When the folding wings on both sides are fully deployed, the position locks on the folding wings lock, and a feedback signal is sent to the control system, and the limit switch 4 is released from the limit state; the wheel brake command is released, and the active brake is released.

[0099] After the active braking is released for a certain period of time (e.g., 5 seconds), the thrust control command is triggered, and the aircraft takeoff procedure is executed.

[0100] When the folding wing operation experiences asymmetry on both sides, folding on one side, failure, or jamming, the folding wing control indicators 5 on both sides will indicate that the folding wing is either folded up or remains in the jammed position.

[0101] At the same time, a command is issued to drive the thrust handle 1 back to the slow position; drive the limit switch 4 and limit unit 3 to reset back to the locked state (the red light of limit switch 4 is on);

[0102] When the aircraft is in the air, the folding wing control indicator 5 is locked, cutting off all control commands, and the limit switch 4 is in the unfolded and locked state (the green light of limit switch 4 is on).

[0103] like Figure 7 As shown, the automatic folding-up process for aircraft landing is as follows:

[0104] When the aircraft touches down, the pilot maneuvers the thrust handle 1 back to idle position;

[0105] At this time, the automatic brake is activated, and the folding wing control indicator 5 is activated (the green light of limit switch 4 flashes);

[0106] If the pilot activates reverse thrust during landing, when the reverse thrust is disengaged and the aircraft's ground speed falls below the speed limit (reference 50 Kn), a command is triggered to actuate the folding wing control indicator 5 and fold the wing. Once fully folded, the limit switch 4 is locked, locking the limit unit and illuminating the red limit switch indicator.

[0107] If the pilot does not activate thrust reverser unit 2 and the ground speed is below 50 knots, double-clicking limit switch 4 triggers a command that drives the folding wing control indicator 5 and the folding wing to fold up. Once fully folded, limit switch 4 is locked, driving limit unit 3 to lock, and the red light on limit switch 4 illuminates.

[0108] The device of this invention provides control over the folding wings of an aircraft. Integrated into a thrust control unit, it controls the folding and unfolding of the wingtips of the folding wing. Simultaneously, when the wingtips are folded, it restricts the pilot's control over thrust, preventing loss of control due to the wingtips not unfolding or locking, thereby improving flight safety.

[0109] While several embodiments of the present invention have been provided herein, those skilled in the art should understand that modifications can be made to these embodiments without departing from the spirit of the invention. The above embodiments are merely exemplary and should not be construed as limiting the scope of the invention.

Claims

1. A thrust control device integrating folding wing control, characterized in that, The device includes a thrust handle, a reverse thrust unit, a limit unit, a limit switch, a folding wing control indicator, and a control system. The thrust handle is used to control the engine speed; The thrust reverser unit is mounted on the thrust handle and is used to turn the engine thrust reverser on or off. The folding wing control indicator is located on the side guards on both sides of the thrust handle, and folds up or unfolds synchronously with the corresponding side of the aircraft folding wing to indicate the folding or unfolding state of the aircraft folding wing. The limiting unit is disposed on the folding wing control indicator and is used to limit the rotation angle of the thrust handle. By limiting the operating stroke of the thrust handle, the engine speed and the aircraft ground taxiing speed are limited. The limit switch is mounted on the thrust handle and is used to control the unlocking and locking of the limit unit; The control system is connected to the thrust handle, the reverse thrust unit, the limit unit, the limit switch, and the folding wing control indicator signal, respectively.

2. The thrust control device with integrated folding wing control as described in claim 1, characterized in that, The folding wing control indicator is a sheet-like or thin block-like structure, connected to the outside of the side guard plate via a first pivot, and can be folded up or unfolded along the first pivot; when folded up, the folding wing control indicator is in close contact with the side guard plate; The folding wing control indicator has a mounting groove, and the limiting unit is installed in the mounting groove; the side guard plate has a first opening corresponding to the limiting unit; when the folding wing control indicator is in the folded state, the limiting unit enters the inside of the side guard plate through the first opening, limiting the thrust handle to rotate within a certain angle range.

3. The thrust control device with integrated folding wing control as described in claim 2, characterized in that, The limiting unit includes a lever with a second rotating shaft, which is disposed in the mounting groove. The initial position of the lever is in the mounting groove, at which time the limiting unit is in an unlocked state. When the lever rotates 90° from its initial position along the second rotating shaft, the lever passes through the first opening and enters the inner side of the side guard plate, limiting the travel range of the thrust handle.

4. The thrust control device with integrated folding wing control as described in claim 3, characterized in that, The device also includes a first motor and a second motor; the first motor drives the folding wing control indicator to rotate around a first rotating shaft, and the second motor drives the toggle block to rotate around a second rotating shaft. Both the first motor and the second motor are signal-connected to the control system.

5. The thrust control device with integrated folding wing control as described in claim 1, characterized in that, The limit switch is equipped with status indicator lights, which respectively indicate the locking and unlocking of the limit unit, and the unfolding and locking of the folding wing.

6. The thrust control device with integrated folding wing control as described in claim 3, characterized in that, A trigger switch is provided on the limiting unit, and a corresponding second opening is provided on the side guard plate. When the limiting unit is folded up, the trigger switch passes through the second opening and enters the inside of the side guard plate. When the push handle passes through the second opening, it triggers the trigger switch.

7. A thrust control method integrating folding wing control, characterized in that, The thrust control device using the integrated folding wing control as described in any one of claims 1-6, the method includes locking the limit unit and unlocking the limit unit; The locking of the limiting unit includes: S1. Operate the limit switch, give a locking command and transmit it to the control system. The control system controls the folding wing to fold up. The corresponding folding wing control indicator folds up synchronously around the first rotating shaft under the drive of the first motor. The folding wing control indicator is in close contact with the side guard plate. S2. The control system determines whether the thrust handle is in the slow position. If not, it controls the thrust handle to return to the slow position. S3. The limiting unit located on the folding wing control indicator rotates around the second rotating shaft under the drive of the second motor. The toggle block of the limiting unit rotates and enters the inner side of the side guard plate through the first opening, limiting the thrust handle to rotate within the set angle range. At this time, the thrust handle only has a partial stroke. The unlocking of the limiting unit includes: X1. Operate the limit switch, give an unlock command and transmit it to the control system. The control system controls the limit unit's toggle block to rotate around the second shaft under the drive of the second motor, and the toggle block is retracted into the mounting slot. X2. The control system controls the unfolding of the folding wings. The corresponding folding wing control indicator rotates synchronously around the first axis under the drive of the first motor, and the thrust handle returns to its full stroke.

8. The thrust control method for integrated folding wing control as described in claim 7, characterized in that, The method is used for high-speed ground taxiing protection and deactivation during aircraft ground taxiing. The ground skidding high-speed protection specifically includes: When the aircraft engine is started, the folding wings are folded up, the limit unit is locked, and the limit switch is in the locked position. When the aircraft's ground speed is lower than the speed limit, the aircraft taxis normally, and the limit unit restricts the rotation angle of the thrust handle to ensure that the aircraft's ground speed is lower than the speed limit. When the aircraft's ground speed exceeds the speed limit, if the limit unit is in a locked state, the status of the limit unit is transmitted to the control system, and the control system drives the thrust handle back to the slow position. The ground taxiing high-speed protection is released as follows: Operate the limit switch and send a limit release command; the limit unit will unlock under the drive of the control system. The thrust handle limit is released, the thrust handle returns to its full travel, and the aircraft ground taxiing speed limit is released.

9. The thrust control method for integrated folding wing control as described in claim 8, characterized in that, The method is used for the coordinated control of engine thrust and folding wings, including manual control and automatic control; The manual control specifically refers to: When the aircraft enters the runway to prepare for takeoff, the ground taxiing high-speed protection is released after the operation is completed. By operating the limit switch, the control system controls the unfolding of the folding wings, and the corresponding folding wing control indicator unfolds synchronously. When the folding wings on both sides are deployed, the position lockers on the folding wings lock, and a feedback signal is sent to the control system. The limit switches are released from their limit states, and the aircraft enters the takeoff procedure. The automatic control specifically refers to: When the aircraft enters the runway to prepare for takeoff, the ground taxiing high-speed protection is released after the operation is completed. Push the thrust handle to the TOGA position. During the movement of the thrust handle, the trigger switch on the limit unit is activated. The trigger switch sends a feedback signal to the control system, which controls the folding wings to unfold. The corresponding folding wing control indicator unfolds synchronously. At the same time, after a thrust control delay, the wheel brake command is triggered, driving the aircraft's main wheels to brake. When the folding wings on both sides are fully deployed, the position locks on the folding wings lock, and a feedback signal is sent to the control system, the limit switches are released from the limit state; the wheel brake command is released, and the main wheel brake is released. After the main wheel brakes have been released for a certain period of time, the thrust control command is triggered, and the aircraft takeoff procedure is executed.

10. The thrust control method for integrated folding wing control as described in claim 9, characterized in that, When the folding wing operation experiences asymmetry on both sides, folding on one side, failure, or jamming, the folding wing control indicators on both sides will indicate whether to drive the folding wing to fold up or stay in the jammed position. Simultaneously, a command is issued to drive the thrust handle back to the slow position; the limit switch and limit unit are reset to the locked state. When the aircraft is in the air, the folding wing control indicator is locked, cutting off all control commands, and the limit switch is in the unfolded and locked state of the folding wings.

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