Aircraft dual-side stick control system and method thereof

Abstract

The present application belongs to the technical field of aircraft dual-sidestick control design, and specifically relates to an aircraft dual-sidestick control system and method thereof, wherein the aircraft dual-sidestick control system is respectively provided with a main sidestick and a secondary sidestick at the pilot position and the co-pilot position of the aircraft, and the main sidestick and the secondary sidestick are respectively equipped with a longitudinal command sensor, a lateral command sensor, an authority switch and an autopilot disconnect button. Based on whether the aircraft autopilot is connected and whether the longitudinal command sensors and lateral command sensors of the main sidestick and the secondary sidestick are in normal state, the aircraft dual-sidestick control mode is switched between the dual-side control mode, the main side locked control mode, the main side temporary control mode, the secondary side locked control mode, and the secondary side temporary control mode through the authority switch of the main sidestick and the secondary sidestick and the autopilot disconnect button, and the aircraft autopilot can be disconnected by control, which can greatly facilitate the pilot and co-pilot to control the aircraft.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft dual-side stick control design, and in particular relates to an aircraft dual-side stick control system and method thereof. Background Art

[0002] The aircraft's control methods can be divided into control wheel control method and side stick control method. Among them, in the dual side stick control method, the main and auxiliary side sticks are arranged on the outer control consoles of the main and co-pilots. There are special armrests on the pilot's seat to provide arm support. Only small wrist movements are required to control the aircraft, which can reduce the pilot's workload. It occupies a small space and will not block the instruments and meters in front of the pilot. It is used in fly-by-wire aircraft and has outstanding advantages over the control wheel control method.

[0003] Currently, in the dual-sidestick control mode, the main and auxiliary sidesticks arranged on the outer control consoles of the main and co-pilot can be operated independently and cannot be linked. The distribution of control authority is unclear, and there is no reverse drive during automatic driving, which brings inconvenience to the main and co-pilot's operation.

[0004] This application is proposed in view of the above-mentioned technical defects.

[0005] It should be noted that the disclosure of the above background technology content is only used to assist in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above content has been disclosed on the filing date of this application, the above background technology should not be used to evaluate the novelty and creativity of this application. Summary of the Invention

[0006] The purpose of the present application is to provide an aircraft dual-side stick control system and method thereof to overcome or alleviate at least one of the existing technical deficiencies.

[0007] The technical solution of this application is:

[0008] On the one hand, a method for controlling an aircraft with two side sticks is provided, comprising:

[0009] A main side stick is set at the main pilot's position of the aircraft. The main side stick is equipped with a longitudinal command sensor, a lateral command sensor, an authority switch and an autopilot disconnect button;

[0010] A secondary side stick is set at the co-pilot position of the aircraft, and is equipped with a longitudinal command sensor, a lateral command sensor, an authority switch and an autopilot disconnect button;

[0011] The dual side stick control of the aircraft is designed to have:

[0012] In the bilateral control mode, the control displacement is the algebraic sum of the displacements of the main side stick and the auxiliary side stick, and the maximum does not exceed the stroke of the main side stick and the auxiliary side stick;

[0013] The main side is locked in the control mode, and the control displacement is the displacement of the main side stick;

[0014] Temporary control mode of the main side, the control displacement is the displacement of the main side rod;

[0015] In the secondary side locked control mode, the control displacement is the displacement of the secondary side stick;

[0016] Auxiliary side temporary control mode, the control displacement is the displacement of the auxiliary side stick;

[0017] When the aircraft's autopilot is not engaged, if the longitudinal command sensors and lateral command sensors of the primary and secondary sidesticks are in normal condition, and the aircraft's dual-sidestick control method is in dual-side control mode, secondary-side locked control mode, or secondary-side temporary control mode, if the primary sidestick's authority switch and its autopilot disconnect button are pressed within the operating mode switching response time, the aircraft's dual-sidestick control method switches to the primary-side temporary control mode. After releasing the authority switch and its autopilot disconnect button, the aircraft's dual-sidestick control method switches to the dual-side control mode.

[0018] When the aircraft's autopilot is not engaged, if the longitudinal command sensors and lateral command sensors of the primary and secondary sidesticks are in normal condition, if the primary sidestick's authority switch and its autopilot disconnect button are pressed for more than the operating mode switching response time, the aircraft's dual-sidestick control method switches to the primary side locked control mode. After releasing the authority switch and its autopilot disconnect button, the aircraft's dual-sidestick control method remains in the primary side locked control mode. After pressing the authority switch and its autopilot disconnect button again, the aircraft's dual-sidestick control method switches to the dual-side control mode.

[0019] When the aircraft's autopilot is not engaged, if the longitudinal command sensors and lateral command sensors of the primary and secondary sidesticks are in normal condition, and the aircraft's dual-sidestick control method is in dual-side control mode, primary-side locked control mode, or primary-side temporary control mode, if the secondary sidestick's authority switch and its autopilot disconnect button are pressed within the operating mode switching response time, the aircraft's dual-sidestick control method switches to the secondary-side temporary control mode. After releasing the authority switch and its autopilot disconnect button, the aircraft's dual-sidestick control method switches to the dual-side control mode.

[0020] When the aircraft's autopilot is not engaged, if the longitudinal command sensors and lateral command sensors of the primary and secondary sidesticks are in normal condition, if the secondary sidestick's authority switch and its autopilot disconnect button are pressed for more than the operating mode switching response time, the aircraft's dual sidestick control method switches to the secondary side lock control mode. After releasing the authority switch and its autopilot disconnect button, the aircraft's dual sidestick control method remains in the secondary side lock control mode. After pressing the authority switch and its autopilot disconnect button again, the aircraft's dual sidestick control method switches to the dual side control mode.

[0021] When the aircraft's autopilot is not engaged, if the longitudinal and lateral command sensors of the primary and secondary sidesticks are in normal condition, the control mode of the aircraft's dual-sidestick control method will not change if the primary and secondary sidestick authority switches and their autopilot disconnect buttons are pressed simultaneously;

[0022] When the aircraft autopilot is not engaged, if the longitudinal command sensor or lateral command sensor of the primary side stick is in a faulty state, the aircraft's dual side stick control method switches to the secondary side lock control mode;

[0023] When the aircraft autopilot is not engaged, if the longitudinal command sensor or lateral command sensor of the secondary sidestick is in a faulty state, the aircraft's dual sidestick control method switches to the primary side locked control mode;

[0024] When the aircraft autopilot is connected, press the authority switch of the primary or secondary sidestick and the autopilot disconnect button, the aircraft autopilot is disconnected, and the aircraft dual sidestick control method is restored to the control mode before the aircraft autopilot is connected. The aircraft autopilot disconnect alarm sounds, and press the authority switch of the primary or secondary sidestick and the autopilot disconnect button again to clear the aircraft autopilot disconnect alarm.

[0025] According to at least one embodiment of the present application, in the above-mentioned aircraft dual-side stick control method, the operating mode switching response time is 30 seconds.

[0026] According to at least one embodiment of the present application, in the above-mentioned aircraft dual sidestick control method, the main sidestick is further configured with a pitch trim switch;

[0027] The secondary sidestick is also equipped with a pitch trim switch;

[0028] The aircraft's dual side stick controls are:

[0029] In the dual-side control mode, the pitch trim command adopts the OR logic of the pitch trim switch commands of the primary side stick and the secondary side stick;

[0030] When the master side is in locked control mode, the pitch trim command adopts the command of the master side stick pitch trim switch;

[0031] When the master side is in temporary control mode, the pitch trim command adopts the command of the master side stick pitch trim switch;

[0032] When the secondary side is locked in control mode, the pitch trim command adopts the command of the secondary side stick pitch trim switch;

[0033] When the secondary side is in temporary control mode, the pitch trim command adopts the command of the secondary side stick pitch trim switch.

[0034] According to at least one embodiment of the present application, in the above-mentioned aircraft dual sidestick control method, the master sidestick is further configured with an authority indicator light;

[0035] The secondary side stick is also equipped with an authority indicator light;

[0036] The aircraft's dual side stick controls are:

[0037] In the double-side control mode, the main side stick and auxiliary side stick authority indicator lights are off;

[0038] When the master side is in locked control mode, the master side stick authority indicator light goes out and the slave side stick authority indicator lights up;

[0039] When the master side is in temporary control mode, the master side stick authority indicator light goes out and the slave side stick authority indicator lights up;

[0040] When the secondary side is locked in the control mode, the secondary side stick authority indicator light goes out and the primary side stick authority indicator lights up;

[0041] When the secondary side is in temporary control mode, the secondary side stick authority indicator light goes out and the primary side stick authority indicator lights up.

[0042] According to at least one embodiment of the present application, in the above-mentioned aircraft dual-sidestick control method, the primary sidestick is further configured with a contralateral sidestick non-neutral signal light, which lights up when the secondary sidestick deviates from the neutral position and goes out when the secondary sidestick returns to the neutral position;

[0043] The secondary side stick is also equipped with an opposite side stick non-neutral signal light, which lights up when the main side stick deviates from the neutral position and goes out when the main side stick returns to the neutral position.

[0044] Another aspect provides an aircraft dual sidestick control system, comprising:

[0045] The main side stick is located at the main pilot's position and is equipped with a longitudinal command sensor, a lateral command sensor, an authority switch, and an autopilot disconnect button.

[0046] The secondary side stick is located at the co-pilot position of the aircraft and is equipped with a longitudinal command sensor, a lateral command sensor, an authority switch, and an autopilot disconnect button;

[0047] The aircraft's dual sidestick control system has:

[0048] In the bilateral control mode, the control displacement is the algebraic sum of the displacements of the main side stick and the auxiliary side stick, and the maximum does not exceed the stroke of the main side stick and the auxiliary side stick;

[0049] The main side is locked in the control mode, and the control displacement is the displacement of the main side stick;

[0050] Temporary control mode of the main side, the control displacement is the displacement of the main side rod;

[0051] In the secondary side locked control mode, the control displacement is the displacement of the secondary side stick;

[0052] Auxiliary side temporary control mode, the control displacement is the displacement of the auxiliary side stick;

[0053] When the aircraft's autopilot is not engaged, if the longitudinal command sensors and lateral command sensors of the primary and secondary sidesticks are in normal condition, and the aircraft's dual-sidestick control system is in dual-side control mode, secondary-side locked control mode, or secondary-side temporary control mode, if the primary sidestick's authority switch and its autopilot disconnect button are pressed within the operating mode switching response time, the aircraft's dual-sidestick control system switches to the primary-side temporary control mode. After the authority switch and its autopilot disconnect button are released, the aircraft's dual-sidestick control system switches to the dual-side control mode.

[0054] When the aircraft's autopilot is not engaged, if the longitudinal command sensors and lateral command sensors of the primary and secondary sidesticks are in normal condition, if the authority switch of the primary sidestick and its autopilot disconnect button are pressed for more than the operating mode switching response time, the aircraft's dual sidestick control system switches to the primary side locked control mode. After releasing the authority switch and its autopilot disconnect button, the aircraft's dual sidestick control system remains in the primary side locked control mode. After pressing the authority switch and its autopilot disconnect button again, the aircraft's dual sidestick control system switches to the dual side control mode.

[0055] When the aircraft's autopilot is not engaged, if the longitudinal command sensors and lateral command sensors of the primary and secondary sidesticks are in normal condition, and the aircraft's dual-sidestick control system is in dual-side control mode, primary-side locked control mode, or primary-side temporary control mode, if the secondary sidestick's authority switch and its autopilot disconnect button are pressed within the operating mode switching response time, the aircraft's dual-sidestick control system switches to the secondary-side temporary control mode. After the authority switch and its autopilot disconnect button are released, the aircraft's dual-sidestick control system switches to the dual-side temporary control mode.

[0056] When the aircraft's autopilot is not engaged, if the longitudinal command sensors and lateral command sensors of the primary and secondary sidesticks are in normal condition, if the authority switch of the secondary sidestick and its autopilot disconnect button are pressed for more than the operating mode switching response time, the aircraft's dual sidestick control system switches to the secondary side locked control mode. After releasing the authority switch and its autopilot disconnect button, the aircraft's dual sidestick control system remains in the secondary side locked control mode. After pressing the authority switch and its autopilot disconnect button again, the aircraft's dual sidestick control system switches to the dual side control mode.

[0057] When the aircraft's autopilot is not engaged, if the longitudinal and lateral command sensors of the primary and secondary sidesticks are in normal condition, the control mode of the aircraft's dual-sidestick control system will not change if the authority switch buttons of the primary and secondary sidesticks and their autopilot disconnect buttons are pressed simultaneously;

[0058] When the aircraft autopilot is not engaged, if the longitudinal command sensor or lateral command sensor of the primary side stick is in a faulty state, the aircraft's dual side stick control system switches to the secondary side lock control mode;

[0059] When the aircraft autopilot is not engaged, if the longitudinal command sensor or lateral command sensor of the secondary sidestick is in a faulty state, the aircraft's dual sidestick control system switches to the primary side locked control mode;

[0060] When the aircraft is autopiloted, press the authority switch of the primary or secondary sidestick and the autopilot disconnect button. The aircraft autopilot will be disconnected, and the aircraft's dual sidestick control system will return to the control mode before the aircraft autopilot was connected. The aircraft autopilot disconnect alarm will sound. Press the authority switch of the primary or secondary sidestick and the autopilot disconnect button again to clear the aircraft autopilot disconnect alarm.

[0061] According to at least one embodiment of the present application, in the above-mentioned aircraft dual-sidestick control system, the operating mode switching response time is 30s.

[0062] According to at least one embodiment of the present application, in the above-mentioned aircraft dual-side stick control system,

[0063] The main sidestick is also equipped with a pitch trim switch;

[0064] The secondary sidestick is also equipped with a pitch trim switch;

[0065] The aircraft's dual side stick control system is:

[0066] In the dual-side control mode, the pitch trim command adopts the OR logic of the pitch trim switch commands of the primary side stick and the secondary side stick;

[0067] When the master side is in locked control mode, the pitch trim command adopts the command of the master side stick pitch trim switch;

[0068] When the master side is in temporary control mode, the pitch trim command adopts the command of the master side stick pitch trim switch;

[0069] When the secondary side is locked in control mode, the pitch trim command adopts the command of the secondary side stick pitch trim switch;

[0070] When the secondary side is in temporary control mode, the pitch trim command adopts the command of the secondary side stick pitch trim switch.

[0071] According to at least one embodiment of the present application, in the above-mentioned aircraft dual sidestick control system, the master sidestick is further configured with an authority indicator light;

[0072] The secondary side stick is also equipped with an authority indicator light;

[0073] The aircraft's dual side stick control system is:

[0074] In the double-side control mode, the main side stick and auxiliary side stick authority indicator lights are off;

[0075] When the master side is in locked control mode, the master side stick authority indicator light goes out and the slave side stick authority indicator lights up;

[0076] When the master side is in temporary control mode, the master side stick authority indicator light goes out and the slave side stick authority indicator lights up;

[0077] When the secondary side is locked in the control mode, the secondary side stick authority indicator light goes out and the primary side stick authority indicator lights up;

[0078] When the secondary side is in temporary control mode, the secondary side stick authority indicator light goes out and the primary side stick authority indicator lights up.

[0079] According to at least one embodiment of the present application, in the above-mentioned aircraft dual-sidestick control system, the primary sidestick is further configured with a contralateral sidestick non-neutral signal light, which lights up when the secondary sidestick deviates from the neutral position and goes out when the secondary sidestick returns to the neutral position;

[0080] The secondary side stick is also equipped with an opposite side stick non-neutral signal light, which lights up when the main side stick deviates from the neutral position and goes out when the main side stick returns to the neutral position. BRIEF DESCRIPTION OF THE DRAWINGS

[0081] Figure 1 Schematic diagram of an aircraft dual-side stick control system provided in an embodiment of the present application.

[0082] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product; in addition, the drawings are used for illustrative purposes, and their positional relationships are limited to illustrative purposes and cannot be understood as limitations on this patent. DETAILED DESCRIPTION

[0083] To make the technical solution and its advantages of the present application clearer, the technical solution of the present application will be described in further detail below in conjunction with the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of the present application and are only used to explain the present application, not to limit the present application. It should be noted that, for ease of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0084] In addition, unless otherwise defined, the technical or scientific terms used in the description of this application should have the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The words "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer" used in the description of this application are only used to indicate relative directions or positional relationships, and do not imply that the device or component must have a specific orientation, be constructed, or operate in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. Therefore, they should not be understood as limitations on this application. The words "first," "second," "third," and similar terms used in the description of this application are used only for descriptive purposes to distinguish different components and should not be understood to indicate or imply relative importance. The words "one," "an," or "the" used in the description of this application should not be understood as absolute limitations on quantity, but should be understood as meaning the presence of at least one. The words "include" or "comprises" used in the description of this application mean that the element or object listed before the word includes the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0085] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "install", "connect", "connect" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or a connection between two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0086] The following is combined with Figure 1 This application is described in further detail.

[0087] On the one hand, a method for controlling an aircraft with two side sticks is provided, comprising:

[0088] A main side stick 1 is set at the main pilot position of the aircraft. The main side stick 1 is equipped with a longitudinal command sensor, a lateral command sensor, an authority switch and an autopilot disconnect button;

[0089] A secondary side stick 2 is set at the co-pilot position of the aircraft, and the secondary side stick 2 is equipped with a longitudinal command sensor, a lateral command sensor, an authority switch and an autopilot disconnect button;

[0090] The dual side stick control of the aircraft is designed to have:

[0091] In the bilateral control mode, the control displacement is the algebraic sum of the displacements of the main side stick 1 and the auxiliary side stick 2, and the maximum does not exceed the stroke of the main side stick 1 and the auxiliary side stick 2;

[0092] In the main side locking control mode, the control displacement is the displacement of the main side rod 1;

[0093] In the temporary control mode of the main side, the control displacement is the displacement of the main side rod 1;

[0094] Secondary side locked control mode, the control displacement is the displacement of the secondary side rod 2;

[0095] Auxiliary side temporary control mode, the control displacement is the displacement of the auxiliary side rod 2;

[0096] When the aircraft's autopilot is not engaged, if the longitudinal command sensors and lateral command sensors of the primary sidestick 1 and the secondary sidestick 2 are in normal condition, and the aircraft's dual-sidestick control method is in dual-side control mode, secondary-side locked control mode, or secondary-side temporary control mode, if the authority switch of the primary sidestick 1 and its autopilot disconnect button are pressed within the operating mode switching response time, the aircraft's dual-sidestick control method switches to the primary-side temporary control mode. After releasing the authority switch and its autopilot disconnect button, the aircraft's dual-sidestick control method switches to the dual-side control mode.

[0097] When the aircraft's autopilot is not engaged, if the longitudinal command sensors and lateral command sensors of the primary sidestick 1 and secondary sidestick 2 are in normal status, if the authority switch and the autopilot disconnect button of the primary sidestick 1 are pressed for more than the operating mode switching response time, the aircraft's dual-sidestick control method switches to the primary side locked control mode. After releasing the authority switch and the autopilot disconnect button, the aircraft's dual-sidestick control method remains in the primary side locked control mode. After pressing the authority switch and the autopilot disconnect button again, the aircraft's dual-sidestick control method switches to the dual-side control mode.

[0098] When the aircraft's autopilot is not engaged, if the longitudinal command sensors and lateral command sensors of the primary sidestick 1 and the secondary sidestick 2 are in normal condition, and the aircraft's dual-sidestick control method is in dual-side control mode, primary-side locked control mode, or primary-side temporary control mode, if the authority switch on the secondary sidestick 2 and its autopilot disconnect button are pressed within the operating mode switching response time, the aircraft's dual-sidestick control method switches to the secondary-side temporary control mode. After releasing the authority switch and its autopilot disconnect button, the aircraft's dual-sidestick control method switches to the dual-side control mode.

[0099] When the aircraft's autopilot is not engaged, if the longitudinal command sensors and lateral command sensors of the primary sidestick 1 and the secondary sidestick 2 are in normal status, if the authority switch and the autopilot disconnect button of the secondary sidestick 2 are pressed for more than the operating mode switching response time, the aircraft's dual-sidestick control method switches to the secondary side-locked control mode. After releasing the authority switch and the autopilot disconnect button, the aircraft's dual-sidestick control method remains in the secondary side-locked control mode. After pressing the authority switch and the autopilot disconnect button again, the aircraft's dual-sidestick control method switches to the dual-side control mode.

[0100] When the aircraft's autopilot is not engaged, if the longitudinal command sensors and lateral command sensors of the primary and secondary sidesticks 1 and 2 are in normal status, if the authority switches of the primary and secondary sidesticks 1 and 2 and their autopilot disconnect buttons are pressed simultaneously, the control mode of the aircraft's dual-sidestick control method will not change;

[0101] When the aircraft autopilot is not engaged, if the longitudinal command sensor or lateral command sensor of the primary side stick 1 is in a faulty state, the aircraft's dual side stick control method switches to the secondary side lock control mode;

[0102] When the aircraft autopilot is not engaged, if the longitudinal command sensor or lateral command sensor of the secondary sidestick 2 is in a faulty state, the aircraft dual sidestick control method switches to the primary side lock control mode;

[0103] When the aircraft's autopilot is connected, press the authority switch of the primary sidestick 1 or the secondary sidestick 2 and its autopilot disconnect button, the aircraft's autopilot is disconnected, and the aircraft's dual-sidestick control method is restored to the control mode before the aircraft's autopilot is connected. The aircraft's autopilot disconnect alarm sounds. At this time, the control mode of the aircraft's dual-sidestick control cannot be switched through the authority switch of the primary sidestick 1 or the secondary sidestick 2 and its autopilot disconnect button. Press the authority switch of the primary sidestick 1 or the secondary sidestick 2 and its autopilot disconnect button again to clear the aircraft's autopilot disconnect alarm. At this time, the control mode of the aircraft's dual-sidestick control can be switched through the authority switch of the primary sidestick 1 or the secondary sidestick 2 and its autopilot disconnect button.

[0104] As for the aircraft dual-sidestick control method disclosed in the above embodiment, those skilled in the art will understand that a main sidestick 1 and a secondary sidestick 2 are respectively provided at the pilot and co-pilot positions of the aircraft, and longitudinal command sensors, lateral command sensors, authority switches and autopilot disconnect buttons are respectively configured on the main sidestick 1 and the secondary sidestick 2. Based on whether the aircraft autopilot is engaged and whether the longitudinal command sensors and lateral command sensors of the main sidestick 1 and the secondary sidestick 2 are in normal states, the aircraft dual-sidestick control modes are switched among the dual-side control mode, the main-side locked control mode, the main-side temporary control mode, the secondary-side locked control mode and the secondary-side temporary control mode through the authority switches of the main sidestick 1 and the secondary sidestick 2 and the autopilot disconnect buttons. The aircraft autopilot can also be disconnected by manipulation, which can greatly facilitate the pilot and co-pilot's control of the aircraft.

[0105] In some optional embodiments, in the above-mentioned aircraft dual-side stick control method, the operating mode switching response time is 30 seconds.

[0106] In some optional embodiments, in the above-mentioned aircraft dual-sidestick control method, the main sidestick 1 is further equipped with a pitch trim switch;

[0107] The secondary side stick 2 is also equipped with a pitch trim switch;

[0108] The aircraft's dual side stick controls are:

[0109] In the dual-side control mode, the pitch trim command adopts the OR logic of the pitch trim switch commands of the primary side stick 1 and the secondary side stick 2;

[0110] When the master side is in locked control mode, the pitch trim command adopts the command of the master side stick 1 pitch trim switch;

[0111] When the master side is in temporary control mode, the pitch trim command adopts the command of the master side stick 1 pitch trim switch;

[0112] When the secondary side is in locked control mode, the pitch trim command adopts the command of the secondary side stick 2 pitch trim switch;

[0113] When the secondary side is in temporary control mode, the pitch trim command adopts the command of the secondary side stick 2 pitch trim switch.

[0114] In some optional embodiments, in the above-mentioned aircraft dual side stick control method, the master side stick 1 is further configured with an authority indicator light;

[0115] The secondary sidebar 2 is also equipped with an authority indicator light;

[0116] The aircraft's dual side stick controls are:

[0117] In the double-side control mode, the authority indicators of the main side stick 1 and the auxiliary side stick 2 are off;

[0118] When the master side is in locked control mode, the master side stick 1 authority indicator light goes out, and the slave side stick 2 authority indicator lights up;

[0119] When the master side is in temporary control mode, the master side stick 1 authority indicator light goes out, and the slave side stick 2 authority indicator lights up;

[0120] When the secondary side is locked in the control mode, the secondary side stick 2 authority indicator light goes out and the primary side stick 1 authority indicator lights up;

[0121] When the secondary side is in temporary control mode, the secondary side stick 2 authority indicator light goes out and the main side stick 1 authority indicator lights up.

[0122] As will be understood by those skilled in the art regarding the dual-sidestick control method for an aircraft disclosed in the above embodiment, the primary sidestick 1 and the secondary sidestick 2 are designed to be equipped with authority indicators to indicate the control authority of the primary sidestick 1 and the secondary sidestick 2, thereby facilitating the primary and secondary pilots to identify the dual-sidestick control modes of the aircraft and facilitating the flight of the aircraft.

[0123] In some optional embodiments, in the above-mentioned aircraft dual-sidestick control method, the primary sidestick 1 is further equipped with a contralateral sidestick non-neutral signal light, which lights up when the secondary sidestick 2 deviates from the neutral position and goes out when the secondary sidestick 2 returns to the neutral position;

[0124] The secondary side stick 2 is also equipped with an opposite side stick non-neutral signal light, which lights up when the main side stick 1 deviates from the neutral position and goes out when the main side stick 1 returns to the neutral position.

[0125] As will be understood by those skilled in the art regarding the dual-sidestick control method for an aircraft disclosed in the above-mentioned embodiment, the design thereof is such that the primary sidestick 1 and the secondary sidestick 2 are provided with opposite-side non-neutral signal lights to indicate whether the primary sidestick 1 and the secondary sidestick 2 have deviated from the neutral position, thereby facilitating the primary and secondary pilots to identify the position states of the primary sidestick 1 and the secondary sidestick 2 and facilitate piloting the aircraft.

[0126] Another aspect provides an aircraft dual sidestick control system, comprising:

[0127] The main side stick 1 is set at the main pilot position of the aircraft and is equipped with a longitudinal command sensor, a lateral command sensor, an authority switch and an autopilot disconnect button;

[0128] Secondary side stick 2, set at the co-pilot position of the aircraft, is equipped with a longitudinal command sensor, a lateral command sensor, an authority switch and an autopilot disconnect button;

[0129] The aircraft's dual sidestick control system has:

[0130] In the bilateral control mode, the control displacement is the algebraic sum of the displacements of the main side stick 1 and the auxiliary side stick 2, and the maximum does not exceed the stroke of the main side stick 1 and the auxiliary side stick 2;

[0131] In the main side locking control mode, the control displacement is the displacement of the main side rod 1;

[0132] In the temporary control mode of the main side, the control displacement is the displacement of the main side rod 1;

[0133] Secondary side locked control mode, the control displacement is the displacement of the secondary side rod 2;

[0134] Auxiliary side temporary control mode, the control displacement is the displacement of the auxiliary side rod 2;

[0135] When the aircraft's autopilot is not engaged, if the longitudinal command sensors and lateral command sensors of the primary sidestick 1 and the secondary sidestick 2 are in normal condition, and the aircraft's dual-sidestick control system is in dual-side control mode, secondary-side locked control mode, or secondary-side temporary control mode, if the authority switch on the primary sidestick 1 and its autopilot disconnect button are pressed within the operating mode switching response time, the aircraft's dual-sidestick control system switches to the primary-side temporary control mode. After releasing the authority switch and its autopilot disconnect button, the aircraft's dual-sidestick control system switches to the dual-side control mode.

[0136] When the aircraft's autopilot is not engaged, if the longitudinal command sensors and lateral command sensors of the primary sidestick 1 and the secondary sidestick 2 are in normal status, if the authority switch and the autopilot disconnect button of the primary sidestick 1 are pressed for more than the operating mode switching response time, the aircraft's dual sidestick control system switches to the primary side locked control mode. After releasing the authority switch and the autopilot disconnect button, the aircraft's dual sidestick control system remains in the primary side locked control mode. After pressing the authority switch and the autopilot disconnect button again, the aircraft's dual sidestick control system switches to the dual side control mode.

[0137] When the aircraft's autopilot is not engaged, if the longitudinal command sensors and lateral command sensors of the primary sidestick 1 and the secondary sidestick 2 are in normal condition, and the aircraft's dual-sidestick control system is in dual-side control mode, primary-side locked control mode, or primary-side temporary control mode, if the authority switch on the secondary sidestick 2 and its autopilot disconnect button are pressed within the operating mode switching response time, the aircraft's dual-sidestick control system switches to the secondary-side temporary control mode. After releasing the authority switch and its autopilot disconnect button, the aircraft's dual-sidestick control system switches to the dual-side temporary control mode.

[0138] When the aircraft's autopilot is not engaged, if the longitudinal command sensors and lateral command sensors of the primary sidestick 1 and the secondary sidestick 2 are in normal condition, if the authority switch and the autopilot disconnect button of the secondary sidestick 2 are pressed for more than the operating mode switching response time, the aircraft's dual sidestick control system switches to the secondary side locked control mode. After releasing the authority switch and the autopilot disconnect button, the aircraft's dual sidestick control system remains in the secondary side locked control mode. After pressing the authority switch and the autopilot disconnect button again, the aircraft's dual sidestick control system switches to the dual side control mode.

[0139] When the aircraft's autopilot is not engaged, if the longitudinal command sensors and lateral command sensors of the primary sidestick 1 and secondary sidestick 2 are in normal status, if the authority switch buttons of the primary sidestick 1 and secondary sidestick 2 and their autopilot disconnect buttons are pressed simultaneously, the control mode of the aircraft's dual sidestick control system will not change;

[0140] When the aircraft autopilot is not engaged, if the longitudinal command sensor or lateral command sensor of the primary side stick 1 is in a faulty state, the aircraft's dual side stick control system switches to the secondary side lock control mode;

[0141] When the aircraft autopilot is not engaged, if the longitudinal command sensor or lateral command sensor of the secondary sidestick 2 is in a faulty state, the aircraft dual sidestick control system switches to the primary side locked control mode;

[0142] When the aircraft autopilot is connected, press the authority switch of the main sidestick 1 or the auxiliary sidestick 2 and the autopilot disconnect button, the aircraft autopilot is disconnected, the aircraft dual sidestick control system returns to the control mode before the aircraft autopilot is connected, and the aircraft autopilot disconnect alarm is sounded. Press the authority switch of the main sidestick 1 or the auxiliary sidestick 2 and the autopilot disconnect button again to clear the aircraft autopilot disconnect alarm.

[0143] In some optional embodiments, in the above-mentioned aircraft dual-side stick control system, the operating mode switching response time is 30s.

[0144] In some optional embodiments, in the above-mentioned aircraft dual-side stick control system,

[0145] The main side stick 1 is also equipped with a pitch trim switch;

[0146] The secondary side stick 2 is also equipped with a pitch trim switch;

[0147] The aircraft's dual side stick control system is:

[0148] In the dual-side control mode, the pitch trim command adopts the OR logic of the pitch trim switch commands of the primary side stick 1 and the secondary side stick 2;

[0149] When the master side is in locked control mode, the pitch trim command adopts the command of the master side stick 1 pitch trim switch;

[0150] When the master side is in temporary control mode, the pitch trim command adopts the command of the master side stick 1 pitch trim switch;

[0151] When the secondary side is in locked control mode, the pitch trim command adopts the command of the secondary side stick 2 pitch trim switch;

[0152] When the secondary side is in temporary control mode, the pitch trim command adopts the command of the secondary side stick 2 pitch trim switch.

[0153] In some optional embodiments, in the above-mentioned aircraft dual-sidestick control system, the main sidestick 1 is further equipped with an authority indicator light;

[0154] The secondary sidebar 2 is also equipped with an authority indicator light;

[0155] The aircraft's dual side stick control system is:

[0156] In the double-side control mode, the authority indicators of the main side stick 1 and the auxiliary side stick 2 are off;

[0157] When the master side is in locked control mode, the master side stick 1 authority indicator light goes out, and the slave side stick 2 authority indicator lights up;

[0158] When the master side is in temporary control mode, the master side stick 1 authority indicator light goes out, and the slave side stick 2 authority indicator lights up;

[0159] When the secondary side is locked in the control mode, the secondary side stick 2 authority indicator light goes out and the primary side stick 1 authority indicator lights up;

[0160] When the secondary side is in temporary control mode, the secondary side stick 2 authority indicator light goes out and the main side stick 1 authority indicator lights up.

[0161] In some optional embodiments, in the above-mentioned aircraft dual-sidestick control system, the primary sidestick 1 is further provided with a contralateral sidestick non-neutral signal light, which lights up when the secondary sidestick 2 deviates from the neutral position and goes out when the secondary sidestick 2 returns to the neutral position;

[0162] The secondary side stick 2 is also equipped with an opposite side stick non-neutral signal light, which lights up when the main side stick 1 deviates from the neutral position and goes out when the main side stick 1 returns to the neutral position.

[0163] The aircraft dual-sidestick control system disclosed in the above embodiment is an implementation of the aircraft dual-sidestick control method disclosed in the above embodiment. The description is relatively simple. For specific related details, please refer to the description of the relevant part of the aircraft dual-sidestick control method. Its technical effects can also refer to the technical effects of the relevant part of the aircraft dual-sidestick control method, and will not be repeated here.

[0164] In addition, those skilled in the art should also be able to appreciate that the functions of the various unit components of the aircraft dual-sidestick control system disclosed in the embodiments of the present application can be implemented by electronic hardware, computer software, or a combination of the two. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art may choose to adopt different methods to implement the described functions for each specific application and its actual constraints, but such implementation should not be considered to be beyond the scope of this application.

[0165] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to in detail.

[0166] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. A method for controlling an aircraft with two side sticks, characterized in that: include: A main side stick (1) is provided at the main pilot position of the aircraft, and the main side stick (1) is equipped with a longitudinal command sensor, a lateral command sensor, an authority switch and an autopilot disconnect button; A secondary side stick (2) is provided at the co-pilot position of the aircraft, and the secondary side stick (2) is equipped with a longitudinal command sensor, a lateral command sensor, an authority switch and an autopilot disconnect button; The dual side stick control of the aircraft is designed to have: In the double-sided control mode, the control displacement is the algebraic sum of the displacements of the main side rod (1) and the auxiliary side rod (2), and the maximum does not exceed the stroke of the main side rod (1) and the auxiliary side rod (2); The main side is locked in the control mode, and the control displacement is the displacement of the main side rod (1); The temporary control mode of the main side, the control displacement is the displacement of the main side rod (1); Secondary side locking control mode, the control displacement is the displacement of the secondary side rod (2); Auxiliary side temporary control mode, the control displacement is the displacement of the auxiliary side rod (2); In the case where the aircraft autopilot is not connected, if the longitudinal command sensors and lateral command sensors of the main side stick (1) and the auxiliary side stick (2) are in normal state, and the aircraft dual side stick control method is in the dual side control mode, the auxiliary side locked control mode or the auxiliary side temporary control mode, if the authority switch of the main side stick (1) and its autopilot disconnect button are pressed within the operation mode switching response time, the aircraft dual side stick control method is switched to the main side temporary control mode, and after releasing the authority switch and its autopilot disconnect button, the aircraft dual side stick control method is switched to the dual side control mode; In the case where the aircraft autopilot is not connected, if the longitudinal command sensor and the lateral command sensor of the main side stick (1) and the auxiliary side stick (2) are in a normal state, if the authority switch of the main side stick (1) and its autopilot disconnect button are pressed for more than the operation mode switching response time, the aircraft's dual side stick control method is switched to the main side locked control mode, after releasing the authority switch and its autopilot disconnect button, the aircraft's dual side stick control method remains in the main side locked control mode, after pressing the authority switch and its autopilot disconnect button again, the aircraft's dual side stick control method is switched to the dual side control mode; In the case where the aircraft autopilot is not connected, if the longitudinal command sensors and lateral command sensors of the main side stick (1) and the auxiliary side stick (2) are in normal state, and the aircraft dual-side stick control method is in the dual-side control mode, the main side locked control mode or the main side temporary control mode, if the authority switch of the auxiliary side stick (2) and its autopilot disconnect button are pressed within the operation mode switching response time, the aircraft dual-side stick control method is switched to the auxiliary side temporary control mode, and after releasing the authority switch and its autopilot disconnect button, the aircraft dual-side stick control method is switched to the dual-side control mode; In the case where the aircraft autopilot is not connected, if the longitudinal command sensors and lateral command sensors of the main side stick (1) and the auxiliary side stick (2) are in normal state, if the authority switch of the auxiliary side stick (2) and its autopilot disconnect button are pressed for more than the operation mode switching response time, the aircraft's dual side stick control method is switched to the auxiliary side lock control mode, after releasing the authority switch and its autopilot disconnect button, the aircraft's dual side stick control method remains in the auxiliary side lock control mode, after pressing the authority switch and its autopilot disconnect button again, the aircraft's dual side stick control method is switched to the dual side control mode; In the case where the aircraft autopilot is not connected, if the longitudinal command sensor and the lateral command sensor of the main side stick (1) and the auxiliary side stick (2) are in a normal state, if the authority switch of the main side stick (1) and the auxiliary side stick (2) and the autopilot disconnect button are pressed at the same time, the control mode of the aircraft dual side stick control method does not change; When the aircraft autopilot is not engaged, if the longitudinal command sensor or the lateral command sensor of the main side stick (1) is in a faulty state, the aircraft dual side stick control method switches to the secondary side lock control mode; When the aircraft autopilot is not engaged, if the longitudinal command sensor or the lateral command sensor of the secondary side stick (2) is in a faulty state, the aircraft dual side stick control method switches to the primary side locked control mode; When the aircraft autopilot is connected, press the authority switch of the main side stick (1) or the auxiliary side stick (2) and the autopilot disconnect button, the aircraft autopilot is disconnected, the aircraft dual side stick control method is restored to the control mode before the aircraft autopilot is connected, the aircraft autopilot disconnect alarm is sounded, press the authority switch of the main side stick (1) or the auxiliary side stick (2) and the autopilot disconnect button again to clear the aircraft autopilot disconnect alarm.

2. The aircraft dual-side stick control method according to claim 1, characterized in that: The response time for switching between operating modes is 30s.

3. The aircraft dual-side stick control method according to claim 1, characterized in that: The main side stick (1) is also equipped with a pitch trim switch; The secondary side stick (2) is also equipped with a pitch trim switch; The aircraft's dual side stick controls are: In the double-side control mode, the pitch trim command adopts the OR logic of the pitch trim switch command of the main side stick (1) and the auxiliary side stick (2); When the master side is in the locked control mode, the pitch trim command is the command of the master side stick (1) pitch trim switch; When the master side is in temporary control mode, the pitch trim command adopts the command of the master side stick (1) pitch trim switch; When the secondary side is locked in the control mode, the pitch trim command adopts the command of the pitch trim switch of the secondary side stick (2); When the secondary side is in temporary control mode, the pitch trim command adopts the command of the pitch trim switch of the secondary side stick (2).

4. The aircraft dual-side stick control method according to claim 1, characterized in that: The main sidebar (1) is also equipped with an authority indicator light; The secondary sidebar (2) is also equipped with an authority indicator light; The aircraft's dual side stick controls are: In the double-side control mode, the authority indicator lights of the main side stick (1) and the auxiliary side stick (2) are off; When the main side is locked in the operating mode, the authority indicator light of the main side lever (1) goes out and the authority indicator light of the auxiliary side lever (2) lights up; When the master side is in temporary control mode, the authority indicator light of the master side stick (1) goes out and the authority indicator light of the slave side stick (2) lights up; When the secondary side is locked in the control mode, the authority indicator light of the secondary side stick (2) goes out and the authority indicator light of the main side stick (1) lights up; When the secondary side is in temporary control mode, the authority indicator light of the secondary side stick (2) goes out and the authority indicator light of the main side stick (1) lights up.

5. The aircraft dual-side stick control method according to claim 1, characterized in that: The main side stick (1) is also provided with a non-neutral signal light of the opposite side stick, which lights up when the auxiliary side stick (2) deviates from the neutral position and goes out when the auxiliary side stick (2) returns to the neutral position; The secondary side rod (2) is also provided with a non-neutral signal light for the opposite side rod, which lights up when the primary side rod (1) deviates from the neutral position and goes out when the primary side rod (1) returns to the neutral position.

6. An aircraft dual side stick control system, characterized in that: include: A main side stick (1), which is arranged at the main pilot's position of the aircraft and is equipped with a longitudinal command sensor, a lateral command sensor, an authority switch and an autopilot disconnect button; A secondary side stick (2), which is arranged at the co-pilot position of the aircraft and is equipped with a longitudinal command sensor, a lateral command sensor, an authority switch and an autopilot disconnect button; The aircraft's dual sidestick control system has: In the double-sided control mode, the control displacement is the algebraic sum of the displacements of the main side rod (1) and the auxiliary side rod (2), and the maximum does not exceed the stroke of the main side rod (1) and the auxiliary side rod (2); The main side is locked in the control mode, and the control displacement is the displacement of the main side rod (1); The temporary control mode of the main side, the control displacement is the displacement of the main side rod (1); Secondary side locking control mode, the control displacement is the displacement of the secondary side rod (2); Auxiliary side temporary control mode, the control displacement is the displacement of the auxiliary side rod (2); In the case where the aircraft autopilot is not connected, if the longitudinal command sensors and lateral command sensors of the main side stick (1) and the auxiliary side stick (2) are in normal state, and the aircraft dual side stick control system is in the dual side control mode, the auxiliary side locked control mode or the auxiliary side temporary control mode, if the authority switch of the main side stick (1) and its autopilot disconnect button are pressed within the operation mode switching response time, the aircraft dual side stick control system switches to the main side temporary control mode, and after releasing the authority switch and its autopilot disconnect button, the aircraft dual side stick control system switches to the dual side control mode; In the case where the aircraft autopilot is not connected, if the longitudinal command sensor and the lateral command sensor of the main side stick (1) and the auxiliary side stick (2) are in a normal state, if the authority switch of the main side stick (1) and its autopilot disconnect button are pressed for more than the operation mode switching response time, the aircraft double side stick control system switches to the main side locked control mode, after releasing the authority switch and its autopilot disconnect button, the aircraft double side stick control system remains in the main side locked control mode, after pressing the authority switch and its autopilot disconnect button again, the aircraft double side stick control system switches to the double side control mode; In the case where the aircraft autopilot is not connected, if the longitudinal command sensors and lateral command sensors of the main side stick (1) and the auxiliary side stick (2) are in normal state, and the aircraft dual side stick control system is in the dual side control mode, the main side locked control mode or the main side temporary control mode, if the authority switch of the auxiliary side stick (2) and its autopilot disconnect button are pressed within the operation mode switching response time, the aircraft dual side stick control system switches to the auxiliary side temporary control mode, and after releasing the authority switch and its autopilot disconnect button, the aircraft dual side stick control system switches to the dual side control mode; In the case where the aircraft autopilot is not connected, if the longitudinal command sensors and lateral command sensors of the main side stick (1) and the auxiliary side stick (2) are in normal state, if the authority switch of the auxiliary side stick (2) and its autopilot disconnect button are pressed for more than the operation mode switching response time, the aircraft double side stick control system switches to the auxiliary side lock control mode, after releasing the authority switch and its autopilot disconnect button, the aircraft double side stick control system remains in the auxiliary side lock control mode, after pressing the authority switch and its autopilot disconnect button again, the aircraft double side stick control system switches to the dual side control mode; In the case where the aircraft autopilot is not connected, if the longitudinal command sensor and the lateral command sensor of the main side stick (1) and the auxiliary side stick (2) are in a normal state, if the authority switch of the main side stick (1) and the auxiliary side stick (2) and the autopilot disconnect button are pressed at the same time, the control mode of the aircraft dual side stick control system does not change; When the aircraft autopilot is not engaged, if the longitudinal command sensor or the lateral command sensor of the main side stick (1) is in a faulty state, the aircraft dual side stick control system switches to the secondary side lock control mode; When the aircraft autopilot is not engaged, if the longitudinal command sensor or the lateral command sensor of the secondary side stick (2) is in a faulty state, the aircraft dual side stick control system switches to the primary side locked control mode; When the aircraft autopilot is connected, press the authority switch of the main side stick (1) or the auxiliary side stick (2) and the autopilot disconnect button, the aircraft autopilot is disconnected, the aircraft dual side stick control system returns to the control mode before the aircraft autopilot is connected, and the aircraft autopilot disconnect alarm is sounded. Press the authority switch of the main side stick (1) or the auxiliary side stick (2) and the autopilot disconnect button again to clear the aircraft autopilot disconnect alarm.

7. The aircraft dual side stick control system according to claim 6, characterized in that: The response time for switching between operating modes is 30s.

8. The aircraft dual-side stick control system according to claim 6, characterized in that: The main side stick (1) is also equipped with a pitch trim switch; The secondary side stick (2) is also equipped with a pitch trim switch; The aircraft's dual side stick control system is: In the double-side control mode, the pitch trim command adopts the OR logic of the pitch trim switch command of the main side stick (1) and the auxiliary side stick (2); When the master side is in the locked control mode, the pitch trim command is the command of the master side stick (1) pitch trim switch; When the master side is in temporary control mode, the pitch trim command adopts the command of the master side stick (1) pitch trim switch; When the secondary side is locked in the control mode, the pitch trim command adopts the command of the pitch trim switch of the secondary side stick (2); When the secondary side is in temporary control mode, the pitch trim command adopts the command of the pitch trim switch of the secondary side stick (2).

9. The aircraft dual side stick control system according to claim 6, characterized in that: The main sidebar (1) is also equipped with an authority indicator light; The secondary sidebar (2) is also equipped with an authority indicator light; The aircraft's dual side stick control system is: In the double-side control mode, the authority indicator lights of the main side stick (1) and the auxiliary side stick (2) are off; When the main side is locked in the operating mode, the authority indicator light of the main side lever (1) goes out and the authority indicator light of the auxiliary side lever (2) lights up; When the master side is in temporary control mode, the authority indicator light of the master side stick (1) goes out and the authority indicator light of the slave side stick (2) lights up; When the secondary side is locked in the control mode, the authority indicator light of the secondary side stick (2) goes out and the authority indicator light of the main side stick (1) lights up; When the secondary side is in temporary control mode, the authority indicator light of the secondary side stick (2) goes out and the authority indicator light of the main side stick (1) lights up.

10. The aircraft dual side stick control system according to claim 6, characterized in that: The main side stick (1) is also provided with a non-neutral signal light of the opposite side stick, which lights up when the auxiliary side stick (2) deviates from the neutral position and goes out when the auxiliary side stick (2) returns to the neutral position; The secondary side rod (2) is also provided with a non-neutral signal light for the opposite side rod, which lights up when the primary side rod (1) deviates from the neutral position and goes out when the primary side rod (1) returns to the neutral position.

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