Side lever operating device and operating method thereof

Abstract

A side lever manipulating device and a manipulating method thereof, the side lever manipulating device for controlling pitching motion and rolling motion of an aircraft, comprising: a manipulating handle which is a main body part of the side lever manipulating device and is held by a pilot; a pitch control unit which is provided to the control handle, and which controls the pitch movement of the aircraft by means of the pitch control unit; and a rolling control unit which is provided on the control handle and controls the rolling motion of the aircraft by means of the rolling control unit, the pitch control unit and the rolling control unit being independent from each other and not interfering with each other during operation. The side rod control method is used for controlling the side rod control device. By means of the side rod control device and the control method thereof, pitching and rolling control can be decoupled, independent pitching and rolling control is achieved, and therefore the control problem of cross coupling of the side rod is solved.

Description

Technical Field

[0001] The present invention relates to a side stick control device and a control method thereof, and more particularly to a novel side stick control device and a control method thereof for a cockpit side stick, belonging to the technical field of aircraft cockpit side stick control. Background Art

[0002] An aircraft inevitably needs to perform pitch and roll movements during flight. In the past, pilots generally switched the pitch and roll movements of the aircraft by using the control wheel or side stick in the cockpit.

[0003] The control wheel is a pitch and roll control device commonly used in large aircraft such as civil airliners. Its design is based on the principle of mechanical transmission, and it controls pitch movement and roll movement by pulling it forward and backward and turning it left and right respectively.

[0004] However, roll control using the control wheel has low efficiency and delayed response, and the control wheel needs to be turned a large angle (usually more than 90 degrees) to make the aileron reach the maximum deflection angle. The rotation range is large, and the response of the control surface is delayed, which is not suitable for high maneuverability requirements. In addition, when controlling the roll with the control wheel, the entire arm and shoulder must be rotated, rather than just relying on the wrist or fingers. During long flights (such as transoceanic routes), this large-scale movement may cause strain on the shoulder and back muscles, and the large arm movement range can easily cause muscle fatigue.

[0005] Compared with the control wheel design, the control side stick is widely used in military and civilian aircraft design due to its outstanding advantages such as lighter control system weight, smaller cockpit space, lower maintenance cost, reduced flight workload, and higher comfort. With the increasing maturity and continuous development of fly-by-wire technology, fly-by-wire side stick control devices have gradually become a design trend.

[0006] However, although side stick control has many advantages over steering wheel control, it has a significant problem of cross coupling.

[0007] like Figure 3A and Figure 3B As shown, in the operation of the control wheel 2, the pitch control and the roll control are independent control channels. The roll movement of the aircraft is achieved by turning left and right, and the pitch movement of the aircraft is achieved by pulling forward and backward. Therefore, there will be no cross-coupling caused by the erroneous input of the pitch signal and the roll signal.

[0008] However, if Figure 3CAs shown, in the manipulation of the sidestick 3, although pitch and roll movements are also controlled by the front and rear pull rods and the left and right joysticks, there is no obvious independent relationship between pitch and roll manipulation, which can easily lead to cross-coupling of pitch and roll signals and erroneous operation. Therefore, corresponding indicators and requirements need to be designed into the sidestick, such as the technical requirement that "the sensitivities of the sidestick pitch and roll controls should be compatible so that intentional input to one control axis does not cause unintentional input to the other axis. Cross-coupling exceeding 5% is unacceptable."

[0009] To this end, all current sidestick control systems suffer from unintended cross-coupling between axial control commands to varying degrees. An intended control input in one axis can inadvertently trigger aircraft motion in another axis, acting as a coupled control command in the remaining axes.

[0010] Cross-coupling of axial commands is a major obstacle to high-precision manual control. Normal pilot control stick movements and the acceleration vibration forces acting on the pilot's body and sidestick can inadvertently cause cross-coupling of control commands. This cross-coupling can cause unintended aircraft motion and, in the worst case, can result in flight coning or oscillation.

[0011] In addition, the current side stick control methods mainly include active side stick (Active Side Stick) and passive side stick (Passive Side Stick) two control methods. The main differences between the two are reflected in the force feedback mechanism, control logic, system dependence and two-seat coordination mode.

[0012] Both designs are committed to converting manual commands into precise flight control, but active sidesticks are more inclined to "system-assisted control" while passive sidesticks are more inclined to "direct pilot control."

[0013] Previous sidesticks were mainly passive sidesticks. Due to the lack of real-time force feedback mechanism, the pilot could not truly feel the force status information feedback of the aircraft. In addition, passive sidesticks could not realize the linkage between the pilot and co-pilot sidesticks and AP (autopilot) following function.

[0014] In view of the above-mentioned deficiencies in the existing technology, how to provide a side stick control device and a control method thereof that can decouple the pitch and roll controls, realize independent control of pitch and roll, and solve the problem of side stick cross-coupling control has become a technical problem that needs to be solved urgently. Summary of the Invention

[0015] The present disclosure is made to solve the above-mentioned technical problems, and its purpose is to provide a sidestick control device and a control method thereof. The sidestick control device and the control method thereof can effectively avoid erroneous aircraft control inputs caused by the coupling of sidestick control by decoupling the longitudinal control and lateral control of the sidestick on demand.

[0016] To achieve the objectives of the present disclosure, a sidestick control device is provided. The sidestick control device is used to control the pitch and roll movements of an aircraft. The sidestick control device includes: a joystick, which is the main part of the sidestick control device and is held by the pilot; a pitch control unit, which is provided on the joystick and controls the pitch movement of the aircraft; and a roll control unit, which is provided on the joystick and controls the roll movement of the aircraft. The pitch control unit and the roll control unit are independent of each other and do not interfere with each other during operation.

[0017] According to the above configuration, the pitch and roll motions of the aircraft can be independently controlled by the pitch control unit and the roll control unit provided independently of each other, thereby achieving independent manipulation of the pitch and roll motions and solving the cross-coupling problem of the side sticks.

[0018] Preferably, the pitch control unit is provided on one side of the joystick, and the roll control unit is provided on the other side of the joystick opposite to the pitch control unit.

[0019] According to the above configuration, by arranging the pitch control unit and the roll control unit at different relative positions on the joystick, the driver can easily distinguish between the two during operation, thereby effectively preventing the occurrence of erroneous operation.

[0020] Preferably, the pitch control unit and the roll control unit slide in different directions during operation.

[0021] According to the above configuration, by designing the pitch control unit and the roll control unit to move in different directions during operation, it is possible to further facilitate the driver to distinguish between the two, thereby more effectively preventing the occurrence of erroneous operation.

[0022] Preferably, the pitch control unit and the roll control unit are designed to control the pitch movement and roll movement of the aircraft only when triggered by the pilot when independent pitch control and roll control are required.

[0023] According to the above configuration, by designing the pitch control unit and the roll control unit to be activated only when triggered by the pilot, it is possible to more effectively prevent the occurrence of erroneous operation and form an effective complementary control mode with the conventional sidestick control method.

[0024] Preferably, the side stick control device includes a left side stick control device located on the left side of the cockpit and a right side stick control device located on the right side of the cockpit, the left side stick control device and the right side stick control device can independently control the pitch movement and roll movement of the aircraft, and the left side stick control device and the right side stick control device move synchronously and in conjunction with each other during the operation process.

[0025] According to the above structure, by providing the left and right side lever operating devices independently of each other, the control functions of the left and right side lever operating devices can be integrated, thereby effectively improving the work efficiency during driving operation.

[0026] Preferably, the sidestick control device further includes a sidestick angular displacement sensor, a sidestick driver, and a signal processor. The sidestick angular displacement sensor records angular displacement information of the control handle. The sidestick driver receives control signals from the pitch control unit and the roll control unit and drives the control handle to move. The signal processor receives signal information from the angular displacement sensor and sends the integrated information to the corresponding sidestick driver.

[0027] Preferably, the status signals of the side stick angular displacement sensor and the side stick driver of one of the left side stick operating device and the right side stick operating device are transmitted to the signal processor of the other side, and after being integrated by the signal processor, it is determined whether to actuate the side stick driver of the other side.

[0028] According to the above configuration, the synchronous linkage function of the active side stick can be realized through the communication interaction between the left side stick operating device and the right side stick operating device.

[0029] In addition, the present invention also provides a sidestick control method, which is used to control the sidestick control device as described above. The sidestick control method includes the following control modes: a pitch single-axis control mode, in which the pitch movement of the aircraft is controlled by pressing the pitch control part provided on the above-mentioned control handle; and a roll single-axis control mode, in which the roll movement of the aircraft is controlled by pressing the roll control part provided on the above-mentioned control handle.

[0030] According to the above configuration, in the pitch single-axis control mode and the roll single-axis control mode, the pitch motion and the roll motion of the aircraft are independently controlled by the pitch control unit and the roll control unit provided independently of each other, thereby effectively preventing the occurrence of cross-coupling erroneous operations.

[0031] Preferably, the side stick manipulation method further includes a side stick direct manipulation mode, in which the pitch motion and the roll motion are controlled by directly manipulating the manipulation handle without pressing the pitch control unit and the roll control unit.

[0032] According to the above configuration, pitch and roll movements can be controlled by directly manipulating the joystick without operating the pitch control unit and the roll control unit, which can achieve a variety of control methods and is conducive to improving the driving efficiency during the flight.

[0033] In addition, the present invention also provides an aircraft, in which the side stick control device as described above is provided.

[0034] According to the above configuration, in this aircraft, pitch motion and roll motion can be realized by the pitch control unit and roll control unit that are independent of each other, thereby effectively avoiding the occurrence of conventional erroneous operations due to cross coupling. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] With reference to the above purposes, the technical features of the present invention are clearly described in the following technical solutions, and its advantages are apparent from the following detailed description with reference to the accompanying drawings, which illustrate preferred embodiments of the present invention by way of example without limiting the scope of the inventive concept.

[0036] Figure 1A 1 is a schematic structural diagram showing the pitch control method of the side stick control device of the present invention. Figure 1B This is a schematic structural diagram showing the roll control method of the side stick control device of the present invention.

[0037] Figure 2A is a diagram showing the working principle of the side stick control device of the present invention in the first scenario, Figure 2B 2 is a diagram showing the working principle of the side stick control device of the present invention in the second scenario. Figure 2C 1 is a diagram showing the working principle of the side stick control device of the present invention in the third scenario, Figure 2D 1 is a diagram showing the working principle of the side stick control device of the present invention in the fourth scenario, Figure 2E 1 is a diagram showing the working principle of the side stick control device of the present invention in the fifth scenario.

[0038] Figure 3A is a schematic structural diagram showing roll control by the steering wheel, Figure 3B is a schematic structural diagram showing pitch control by the control wheel, Figure 3C This is a schematic diagram showing the structure of roll and pitch control using a conventional control stick. Explanation of symbols

[0039] 1 side stick control device; 10. Joystick; 101 pitch control buttons; 102 roll control buttons; 11 Left side stick control; 111 left sidebar; 112 Left stick pitch control unit; 113 Left stick roll control unit; 114 Left side pole angular displacement sensor; 115 left side rod driver; 116 Left signal processor; 12 right side stick control; 121 right sidebar; 122 Right stick pitch control unit; 123 Right stick roll control unit; 124 right pole angular displacement sensor; 125 right side rod driver; 126 right signal processor; 13 flight control computer; 2 steering wheels; 3 Operate the sidestick. DETAILED DESCRIPTION

[0040] Reference will now be made in detail to various embodiments of the present invention, examples of which are illustrated in the accompanying drawings.

[0041] Although the present invention is described in conjunction with exemplary embodiments, it should be understood that this description is not intended to limit the invention to the exemplary embodiments described below. On the contrary, the present invention is intended to cover not only the exemplary embodiments, but also various alternatives, modifications, equivalents and other embodiments that may be included within the spirit and scope of the invention as defined by the appended claims. (Overall structure of the sidestick control device)

[0042] Below, refer to Figure 1A and Figure 1B , the overall structure of the side stick control device 1 of the present invention will be described.

[0043] like Figure 1AAs shown, the sidestick control device 1 of the present invention is provided with a pitch control button 101 on the control handle 10. By pressing and sliding the pitch control button 101, the aircraft can be controlled and pitch movement can be achieved. In addition, a sidestick actuator is provided at the lower portion of the control handle 10. The pitch control signal from the pitch control button 101 can drive the sidestick of the sidestick control device 1 to move forward or backward. At the same time, the pitch control signal is transmitted to the sidestick actuator of the control handle 10 on the other side, thereby realizing the bilateral synchronous movement function of the active sidestick.

[0044] like Figure 1B As shown, the sidestick control device 1 of the present invention is provided with a roll control button 102 on the control handle 10. By pressing and sliding the roll control button 102, the aircraft can be controlled and roll motion can be achieved. In addition, a sidestick actuator is provided at the lower portion of the control handle 10. The roll control signal from the roll control button 102 can drive the sidestick of the sidestick control device 1 to move left or right. At the same time, the roll control signal is transmitted to the sidestick actuator of the control handle 10 on the other side, thereby achieving the bilateral synchronous movement function of the active sidestick.

[0045] Furthermore, when the pitch control button 101 or the roll control button 102 is not pressed to control the pitch and roll movements of the aircraft, the sidestick control device 1 is operated in the same manner as a conventional sidestick. When the control handle 10 on one side is moved, the control handle 10 on the other side follows the movement via the sidestick actuator, thereby realizing the bilateral synchronous movement function of the active sidestick.

[0046] Preferably, the pitch control button 101 is provided on one side of the control handle 10 , and the roll control button 102 is provided on the other side of the control handle 10 opposite to the pitch control button 101 .

[0047] Furthermore, it is more preferred that Figure 1A and Figure 1B As shown, the pitch control button 101 slides in the up-down direction, and the roll control button 102 slides in the left-right direction.

[0048] Furthermore, it is more preferred that the pitch control button 101 and the roll control button 102 are designed to slide in the up-down direction and the left-right direction only when pressed by the pilot.

[0049] With this design, the driver can more easily distinguish between the pitch control button 101 and the roll control button 102 , which can effectively prevent misoperation during driving, thereby improving the driver's work efficiency. (Specific structure of the side stick control device)

[0050] Below, refer to Figures 2A to 2E, the specific structure of the side stick control device 1 of the present invention is described.

[0051] like Figures 2A to 2E As shown, the side stick control device 1 of the present invention mainly includes a left side stick control device 11 located on the left side of the cockpit, a right side stick control device 12 located on the right side of the cockpit, and a flight control computer 13 that receives control signals from the left side stick control device 11 and the right side stick control device 12.

[0052] The left stick control device 11 mainly includes a left side stick 111 , a left stick pitch control unit 112 , a left stick roll control unit 113 , a left stick angular displacement sensor 114 , a left stick driver 115 and a left signal processor 116 .

[0053] The right stick control device 12 mainly includes a right side stick 121 , a right stick pitch control unit 122 , a right stick roll control unit 123 , a right stick angular displacement sensor 124 , a right stick driver 125 and a right signal processor 126 .

[0054] The left side stick 111 and the right side stick 121 respectively constitute the main body of the side stick control device 1 held by the driver.

[0055] The left stick pitch control unit 112 and the right stick pitch control unit 122 correspond to the pitch control button 101 and are respectively provided on one side of the left side stick 111 and the right side stick 121 for controlling the pitch movement of the aircraft.

[0056] The left side stick roll control unit 113 and the right side stick roll control unit 123 correspond to the roll control button 102 and are respectively provided on the other side of the left side stick 111 and the right side stick 121 for controlling the roll movement of the aircraft.

[0057] The left side stick angular displacement sensor 114 and the right side stick angular displacement sensor 124 are respectively provided on the left side stick 111 and the right side stick 121 , and are used to follow the movement of the left side stick 111 and the right side stick 121 and send the angular displacement information of the movement to the flight control computer 13 .

[0058] The left side stick driver 115 and the right side stick driver 125 receive control signals from the pitch control unit and the roll control unit, and drive the left side stick 111 and the right side stick 121 to move.

[0059] The left signal processor 116 and the right signal processor 126 receive signal information from the angular displacement sensor of the opposite sidestick control device, receive signal information from the sidestick actuator of the opposite sidestick control device, and receive control surface position feedback signals from the flight control computer, and send the integrated information to the corresponding sidestick actuator on this side.

[0060] In addition, the left stick pitch control unit 112, the left stick roll control unit 113, the left stick angular displacement sensor 114, the left stick driver 115 and the left signal processor 116, and the right stick pitch control unit 122, the right stick roll control unit 123, the right stick angular displacement sensor 124, the right stick driver 125 and the right signal processor 126 are connected to the flight control computer 13 in a manner that allows them to communicate with each other, so as to realize the bilateral synchronous movement function of the active side stick. (How to operate the side stick control device)

[0061] Next, continue to refer to Figures 2A to 2E , a method of operating the side stick control device 1 of the present invention will be described.

[0062] like Figure 2A As shown, when the sidestick control device 1 of the present invention is in a normal state, the left sidestick 111 and the right sidestick 121 are in neutral positions without any external operation. The left sidestick angular displacement sensor 114 of the left sidestick control device 11 and the right sidestick angular displacement sensor 124 of the right sidestick control device 12 output control signals indicating that the sidesticks are in position 0 to the flight control computer 13. After receiving the signals, the flight control computer 13 controls the aircraft to prevent pitch and roll movements.

[0063] At the same time, the signals of the left stick angular displacement sensor 114 and the right stick angular displacement sensor 124 are respectively resolved by the left signal processor 116 and the right signal processor 126, so that the left stick driver 115 and the right stick driver 125 are in an inactive state.

[0064] Furthermore, the left and right stick actuators 115 and 125 are designed to drive the left and right sidesticks 111 and 121, respectively, when activated. When inactivated, they follow the left and right sidesticks 111 and 121, respectively, and the magnitude of the following force can be used to provide feedback of a corresponding following reaction force based on the aircraft's current attitude, facilitating the pilot's ability to perform appropriate control operations.

[0065] like Figure 2B As shown, Figure 2B The diagram shows a scene in which the side stick control device 1 of the present invention is in a state of single-axis pitch control.

[0066] When the aircraft needs to be manipulated to perform pitch movement, the pilot with driving authority on the side (hereinafter, for ease of explanation, the left side is used as an example) presses the left side stick pitch control unit 112 of the left side stick operating device 11 of the left side stick 111 and slides it in the up and down directions.

[0067] If the left stick pitch control unit 112 is slid upward while the button is pressed, the left stick pitch control unit 112 outputs a signal to transmit to the left stick driver 115 and the right stick driver 125 , and activates the left stick driver 115 and the right stick driver 125 .

[0068] After activation, the left side rod driver 115 and the right side rod driver 125 drive the left side rod 111 and the right side rod 121 to move forward synchronously, and the left side rod 111 and the right side rod 121 respectively drive the left side rod angular displacement sensor 114 and the right side rod angular displacement sensor 124 to rotate.

[0069] After the rotation, the left stick angular displacement sensor 114 and the right stick angular displacement sensor 124 send signals to the flight control computer 13 , which implements an upward pitch control to cause the nose of the aircraft to deflect downward (nosedown).

[0070] Similarly, if the button of the left stick pitch control unit 112 is pressed and slid downward, the left stick pitch control unit 112 outputs a signal and transmits it to the left stick driver 115 and the right stick driver 125. After being activated, the left stick driver 115 and the right stick driver 125 drive the left side stick 111 and the right side stick 121 to move backward synchronously, thereby driving the left stick angular displacement sensor 114 and the right stick angular displacement sensor 124 to rotate and send a signal to the flight control computer 13. The flight control computer 13 implements a downward pitch control, thereby causing the nose of the aircraft to tilt upward (nose up).

[0071] like Figure 2C As shown, Figure 2B The diagram shows a scene in which the side stick control device 1 of the present invention is in a state of rolling single-axis control.

[0072] When the aircraft needs to be maneuvered to perform a roll motion, the pilot with control authority on the side (hereinafter, for ease of explanation, the left side is used as an example) presses the left side stick roll control unit 113 of the left side stick operating device 11 of the left side stick 111 and slides it in the left and right directions.

[0073] If the left stick roll control unit 113 is slid to the left while the button is pressed, the left stick roll control unit 113 outputs a signal to transmit it to the left stick driver 115 and the right stick driver 125 , activating the left stick driver 115 and the right stick driver 125 .

[0074] After activation, the left side rod driver 115 and the right side rod driver 125 drive the left side rod 111 and the right side rod 121 to move synchronously to the left, and the left side rod 111 and the right side rod 121 respectively drive the left side rod angular displacement sensor 114 and the right side rod angular displacement sensor 124 to rotate.

[0075] After the rotation, the left stick angular displacement sensor 114 and the right stick angular displacement sensor 124 send signals to the flight control computer 13 , which implements a left roll control to make the nose of the aircraft roll to the left (left roll).

[0076] Similarly, if the button of the left stick roll control unit 113 is pressed and slid to the right, the left stick roll control unit 113 outputs a signal and transmits it to the left stick driver 115 and the right stick driver 125. After being activated, the left stick driver 115 and the right stick driver 125 drive the left sidestick 111 and the right sidestick 121 to move synchronously to the right, thereby driving the left stick angular displacement sensor 114 and the right stick angular displacement sensor 124 to rotate and send a signal to the flight control computer 13. The flight control computer 13 implements the right roll control, thereby causing the nose of the aircraft to roll to the right (right roll).

[0077] In addition, as mentioned above, the left side rod driver 115 and the right side rod driver 125 can drive the left side rod 111 and the right side rod 121 to move only after being activated. There are two activation methods as follows.

[0078] Method 1: The left stick driver 115 or the right stick driver 125 is activated after the left stick pitch control unit 112, the left stick roll control unit 113, the right stick pitch control unit 122, or the right stick roll control unit 123 is pressed.

[0079] Method 2: When the left-side stick pitch control unit 112 and the left-side stick roll control unit 113 are not pressed, the drive signals of the right-side stick angular displacement sensor 124 and the right-side stick driver 125 are comprehensively processed by the left-side signal processor 116 to determine whether the left-side stick driver 115 is activated. Similarly, when the right-side stick pitch control unit 122 and the right-side stick roll control unit 123 are not pressed, the drive signals of the left-side stick angular displacement sensor 114 and the left-side stick driver 115 are comprehensively processed by the right-side signal processor 126 to determine whether the right-side stick driver 125 is activated.

[0080] The system of the side stick control device 1 of the present invention is designed so that the authority of mode 1 is higher than that of mode 2, that is, after pressing the left stick pitch control unit 112, the left stick roll control unit 113, the right stick pitch control unit 122, and the right stick roll control unit 123, the above-mentioned left stick driver 115 and right stick driver 125 can be directly activated.

[0081] like Figure 2D As shown, Figure 2D The diagram shows a scene in which the side stick control device 1 of the present invention is in a state of side stick direct control.

[0082] When the left side stick 111 and the right side stick 121 are needed to directly control the flight attitude of the aircraft, similar to the previous side stick control method, after the control, the control side stick is in Figure 2D In the state shown, the left side rod driver 115 and the right side rod driver 125 are in an inactive state. At this time, the left side rod 111 and the right side rod 121 can be directly manipulated.

[0083] like Figure 2D As shown, the pilot with the driving authority (hereinafter, for ease of explanation, the left side is used as an example) manipulates the left side stick 111. Since the left side stick actuator 115 is in an inactive state, it can follow the movement of the left side stick 111. At this time, the left side stick actuator 115 feeds back the control force according to the movement attitude of the aircraft.

[0084] At the same time, the left side rod angular displacement sensor 114 and the left side rod driver 115 send signals and transmit them to the left signal processor 116. After being processed by the left signal processor 116, the right side rod driver 125 can be activated to drive the right side rod 121 to move.

[0085] As described above, by manipulating the left side stick 111, the left side stick driver 115 and the right side stick driver 125 can be caused to move synchronously, and the right side stick angular displacement sensor 124 of the right side stick 121 can be driven to rotate. The left side stick angular displacement sensor 114 and the right side stick angular displacement sensor 124 output signals and transmit them to the flight control computer 13, thereby realizing the manipulation of the aircraft's motion attitude.

[0086] like Figure 2E As shown, when the sidestick control device 1 of the present invention is in the AP-engaged state, when the AP (Autopilot) is engaged, the system of the sidestick control device 1 of the present invention is designed to activate the left stick driver 115 and the right stick driver 125 through the AP signal, and simultaneously drive the left sidestick 111 and the right sidestick 121 to move according to the AP signal, thereby achieving synchronous movement of the two sidesticks and keeping consistent with the movement attitude of the aircraft. (Technical Effect)

[0087] As described above, according to the sidestick control device 1 of the present invention, by providing the pitch control button 101 and the roll control button 102 independently of each other on the control handle 10, it is possible to achieve independent decoupling control of the pitch movement and the roll movement of the aircraft, and solve the cross-coupling problem of the sidestick.

[0088] In addition, by designing a separate side stick driver for each joystick 10, the linkage function of the active side stick can be more easily realized. After receiving the pitch and roll command signals, the synchronous movement of the two side sticks can be achieved, thereby realizing the linkage function of the active side stick.

[0089] Although the structure and operating principles of the present invention have been described above in conjunction with preferred embodiments, those skilled in the art will recognize that the above examples are for illustrative purposes only and do not limit the present invention. The present invention may be modified and varied within the spirit of the claims, and such modifications and variations shall fall within the scope of protection of the present invention.

Claims

1. A side stick control device (1), said side stick control device (1) being used to control the pitch and roll motions of an aircraft, characterized in that: The sidebar control device (1) comprises: A control handle (10), which is the main part of the side stick control device (1) and is for the pilot to hold; A pitch control unit (101), the pitch control unit (101) being provided on the control handle (10), and controlling the pitch motion of the aircraft through the pitch control unit (101); and A roll control unit (102) is provided on the control handle (10), and the roll motion of the aircraft is controlled by the roll control unit (102). The pitch control unit (101) and the roll control unit (102) are independent of each other and do not interfere with each other during operation.

2. The side stick control device (1) according to claim 1, characterized in that The pitch control unit (101) is provided on one side of the joystick (10), and the roll control unit (102) is provided on the other side of the joystick (10) opposite to the pitch control unit (101).

3. The side stick control device (1) according to claim 2, characterized in that The pitch control unit (101) and the roll control unit (102) perform sliding motions in different directions during manipulation.

4. The side stick control device (1) according to claim 3, characterized in that The pitch control unit (101) and the roll control unit (102) are designed to control the pitch movement and roll movement of the aircraft only when triggered by a pilot when independent pitch control and roll control are required.

5. The side stick control device (1) according to any one of claims 1 to 4, characterized in that The side stick control device (1) comprises a left side stick control device (11) located on the left side of the cockpit and a right side stick control device (12) located on the right side of the cockpit. The left stick control device (11) and the right stick control device (12) can independently control the pitch motion and roll motion of the aircraft, and The left side lever operating device (11) and the right side lever operating device (12) move synchronously and in conjunction with each other during the operating process.

6. The side stick control device (1) according to claim 5, characterized in that The side stick control device (1) further comprises a side stick angular displacement sensor, a side stick driver and a signal processor, The side stick angular displacement sensor records angular displacement information of the joystick (10), the side stick driver receives control signals from the pitch control unit (101) and the roll control unit (102), and drives the joystick (10) to move, and the signal processor receives signal information from the angular displacement sensor and sends the integrated information to the corresponding side stick driver.

7. The side stick control device (1) according to claim 6, characterized in that Status signals of the side stick angular displacement sensor and the side stick driver of one of the left side stick operating device (11) and the right side stick operating device (12) are transmitted to the signal processor of the other side, and after being integrated by the signal processor, it is determined whether to actuate the side stick driver of the other side.

8. A side stick control method for controlling the side stick control device (1) according to any one of claims 1 to 7, characterized in that: The sidestick control method includes the following control modes: a pitch single-axis control mode, in which the pitch movement of the aircraft is controlled by pressing the pitch control portion (101) provided on the control handle (10); as well as A rolling single-axis control mode is provided, in which the rolling motion of the aircraft is controlled by pressing the rolling control part (102) provided on the control handle (10).

9. The side stick control method according to claim 8, wherein: The side stick control method also includes a side stick direct control mode, In the side stick direct control mode, the pitch motion and the roll motion are controlled by directly manipulating the control handle (10) in a state where the pitch control unit (101) and the roll control unit (102) are not pressed.

10. An aircraft, characterized in that: The aircraft is provided with a side stick control device (1) according to any one of claims 1 to 9.

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