Aircraft with a modular electric flight control system

Abstract

The present invention relates to a rotary-wing aircraft (1) comprising a first connector assembly (20) and a second connector assembly (25) connected to a control system (70). During an initialization phase, the control system (70) determines a current configuration among reference configurations by communicating through the first connector assembly (20) and the second connector assembly (25). The plurality of reference configurations include: i) a two-pilot configuration (CONF1) in which two identical and complete sets of human-machine interfaces (45) are connected to the first connector assembly (20) and the second connector assembly (25), respectively; and ii) at least one simplified configuration in which a single complete set of human-machine interfaces (45) is connected to either the first connector assembly (20) or the second connector assembly (25).

Description

Technology Field

[0001] This application claims priority to FR 25 01114 filed on February 4, 2025, the entire contents of which are incorporated herein by reference.

[0002] The present invention relates to an aircraft equipped with a modular electric flight control system.

[0003] Aircraft generally include control components that can be operated by a pilot or co-pilot, and these control components act on aerodynamic control surfaces to control the aircraft.

[0004] Accordingly, a rotary-wing aircraft may be equipped with at least one main rotor that contributes to lift or even thrust. The rotary-wing aircraft may also be equipped with a device that controls movement along the yaw axis. The anti-torque device includes, for example, at least one auxiliary rotor having a small size and a nearly horizontal axis of rotation. Such an auxiliary rotor may include, for example, a standard rotor, a ducted rotor, or even a propeller. Thus, the blades of the various rotors represent controllable aerodynamic control surfaces for maneuvering the rotary-wing aircraft.

[0005] Rotary-wing aircraft generally include a cockpit that accommodates at least one set of human-machine interfaces acting on the pitch of the rotor blades. This set of human-machine interfaces includes a first control member, such as a lever, generally referred to as a "collective pitch lever." Additionally, the set of human-machine interfaces includes a second control member, such as a lever, generally referred to as a "cyclic pitch lever." Finally, the set of human-machine interfaces includes a third control member, such as a rudder bar, for changing the pitch of auxiliary rotor blades.

[0006] In the case of rotary-wing aircraft equipped with electric flight control units, each control component is connected to a control box. Consequently, each control command generated by the operation of a control component is transmitted in the form of an electrical signal emitted from the control box. For example, this electrical signal depends on the amplitude and direction of the movement operated by the control component, or on the operation of a button on the control component.

[0007] A control box is connected to a control system configured to control the position of each aerodynamic control surface, for example, by a wired link. Such a control system may include a processing subassembly that determines a setpoint to be achieved by one or more aerodynamic control surfaces as a function of at least one control command encoded by the control box and the current state of the aircraft. Such a setpoint may be, for example, the pitch angle of a blade, the deflection angle of a flap, or the rotational speed of a rotor or propeller. Finally, the control system includes at least one actuation subassembly that controls an actuator acting directly or indirectly on one or more aerodynamic control surfaces as a function of the setpoint determined by the processing subassembly.

[0008] The aircraft may include a single set of human-machine interfaces for pilots.

[0009] Another type of rotary-wing aircraft, referred to as a "two-pilot aircraft," may include a two-pilot configuration in which a pilot and a co-pilot sit side-by-side. This aircraft includes a human-machine interface set for the pilot and a human-machine interface set for the co-pilot, which are hereinafter referred to as the "pilot human-machine interface set" and the "co-pilot human-machine interface set," respectively. The control components of each type of pilot and co-pilot human-machine interface set are mechanically connected to provide the pilot with the appropriate positioning of the control components. Regulatory restrictions regarding the co-pilot's onboard duty depend on the type of aircraft, particularly the maximum number of passengers. For example, a two-pilot aircraft carrying 9 to 18 passengers may be piloted by a single pilot under "visual flight" conditions. Conversely, a two-pilot aircraft carrying 18 or more passengers requires operation by two pilots. Therefore, many operators select aircraft equipped with a two-pilot configuration and operate them as a single pilot or two pilots depending on the mission. Background Technology

[0010] In this regard, patent document FR 3005032 describes a symmetrical cockpit of a rotary-wing aircraft equipped with side-by-side seats and a side access door.

[0011] Patent document US 2019 / 0161170 A1 describes a control system comprising a central control stick and two handles and two levers each positioned on a side bracket.

[0012] Patent document US 2022 / 0266983 A1 describes a flight control computer system configured to control an aircraft in a primary control mode using a signal generated by a primary sensor assembly in response to the pivot motion of a primary control element. In a secondary control mode, the flight control computer system is configured to control the aircraft using a signal generated by a secondary sensor assembly in response to the rotational motion of a secondary control element.

[0013] Patent document US 2024 / 0010331 A1 describes an aircraft equipped with a mechanical control system, wherein the aircraft is equipped with a pilot's cockpit and is equipped with a first main handle and a first auxiliary handle that slide through the armrest channel and control the blade pitch, respectively, periodically and collectively. A second main handle and a second auxiliary handle may be mounted in the co-pilot's cockpit. All handles are mechanically connected to a mechanical flight control chain.

[0014] Patent document WO2004 / 110860 A1 describes a helicopter having a front module that can be connected to a central module containing essential flight components common to all missions. This main module includes, in particular, an engine, flight control elements, rotor blades, a tail boom, landing gear, and an electrical system. means of solving the problem

[0015] Purpose and Overview of the Invention

[0016] Accordingly, one objective of the present invention is to propose an innovative aircraft equipped with a modular flight control system.

[0017] The present invention relates to a rotary-wing aircraft comprising an electric flight control system, wherein the electric flight control system comprises a control system for controlling at least one aerodynamic control surface as a function of at least one command.

[0018] The electric flight control system comprises a first connector assembly and a second connector assembly connected to the control system by at least one wired link, optionally an electric or optical link. At least one set of human-machine interfaces is reversibly connected to the first connector assembly or the second connector assembly, and the set of human-machine interfaces comprises at least one control member equipped with a control box configured to generate said command after operation on the control member. During each flight, the rotary-wing aircraft has a current configuration selected from a plurality of reference configurations. The control system determines the current configuration from the reference configurations by communicating through the first connector assembly and the second connector assembly during the initialization phase, and said plurality of reference configurations include:

[0019] ― A two-pilot configuration in which two identical and complete sets of human-machine interfaces are connected to a first connector assembly and a second connector assembly, respectively; and

[0020] ― At least one simplified configuration in which a single complete set of human-machine interfaces is connected to one of a first connector assembly and a second connector assembly.

[0021] The rotary-wing aircraft has two connector assemblies that can each be connected to two sets of human-machine interfaces. Each connector assembly includes one or more connectors connected to a control system by one or more wired links. These wired links may take the form, for example, of an electrical and / or optical harness. The control box(s) of the sets of human-machine interfaces to be connected are connected to at least one connector of the first connector assembly or the second connector assembly by at least one wired link, and the function of said connector assembly is to acquire said at least one command and transmit it to the control system.

[0022] Each human-machine interface set may include one or more control members. The expression “complete human-machine interface set” refers to a specific human-machine interface set containing the maximum possible number of control members, unlike a simplified set containing a smaller number of control members, or even only a single control member, as described below. Optionally, control members may be connected to multiple connectors of the same connector assembly.

[0023] Accordingly, during the preparation phase, the operator may install one or two sets of human-machine interfaces, depending on the mission to be performed, thereby configuring the aircraft in a single-pilot configuration, a two-pilot configuration, or even the intermediate configuration described below. To switch from one configuration to another, it is sufficient to attach the corresponding control members to the aircraft and connect them. That is, it is sufficient to connect them to one or more connectors, for example, directly through the wiring of the control members themselves, or indirectly through at least one adaptive wired link. The mechanical connections for attaching the control members may be identical and may include a rapid assembly / disassembly system. Furthermore, the present invention enables the implementation of the same link between the connector and the control system, particularly from one aircraft to another, by utilizing a number / regulation of standardized interconnection signals.

[0024] The control system detects the current configuration and is configured to be parameterized according to this current configuration. The control system can apply control laws that vary depending on the current configuration.

[0025] This architecture represents a conceptual shift that enables the installation of two completely independent control stations in two areas of the aircraft cockpit, which can offer significant advantages in terms of convenience. In a single-pilot configuration, a single set of human-machine interfaces can be placed specifically in one area, thereby freeing up space in, for example, the other area of ​​the cockpit.

[0026] Due to the independence of the control station, it is possible to propose cockpit solutions for rotary-wing aircraft featuring various electric flight control functions, allowing for switching from a preset configuration to another within minutes. Since this switching between control station configurations is performed directly in the rotary-wing aircraft operator's workshop, it offers the significant advantage of eliminating the need for a maintenance center. The operator can adjust the aircraft configuration according to the mission to be performed with minimal fixed positioning.

[0027] Due to this versatility, this architecture allows two control members to be switched from one pilot station independently of another. For example, one pilot station may include two connector subassemblies transversely on both sides of the seat, allowing the same control member to be placed on the right or left side of the seat depending on the preference of the pilot or co-pilot.

[0028] Rotary-wing aircraft may also include one or more of the following features.

[0029] According to one possibility, one or more complete sets of human-machine interfaces may each include a first control member for controlling the pitch of a main rotor blade, a second control member for controlling the pitch of the main rotor blade differently from the first control member, and a third control member for controlling the pitch of an auxiliary rotor blade.

[0030] According to the existing alternative, the first control member may be in the form of a stick that controls the pitch of the main rotor blade to tilt the lift vector, and the second control member may be in the form of a lever that controls the pitch of the main rotor blade to control the reference of the lift vector.

[0031] According to an alternative example of control according to the purpose, the first control member and the second control member may set set values, for example, a speed set value and a bearing or attitude set value, and the control system controls the blade pitch of the main rotor and the auxiliary rotor to achieve this purpose.

[0032] According to one possibility compatible with the previously described possibility, at least one simplified configuration may include a rigid single pilot configuration comprising only one complete set of human-machine interfaces connected to the first connector assembly or the second connector assembly.

[0033] In a strict single-pilot configuration, the co-pilot station is removed. With this configuration, weight can be reduced compared to a two-pilot configuration, and above all, the relevant areas of the cockpit can be reconfigured.

[0034] According to one possibility compatible with the previously described possibility, the at least one simplified configuration may include a complete set of human-machine interfaces connected to one of a first connector assembly and a second connector assembly, and an intermediate configuration having a simplified set of human-machine interfaces connected to the first connector assembly or the second connector assembly that is not connected to the complete set of human-machine interfaces.

[0035] A simplified human-machine interface set includes fewer control elements than a complete human-machine interface set.

[0036] For example, a simplified human-machine interface set includes only a single control element.

[0037] In this case, this control member can be configured to control the aircraft's roll angle, pitch angle, yaw angle, and speed.

[0038] In a simplified configuration, one pilot station is the standard pilot station, and the other is an additional pilot station. The additional station is significantly simplified, for example, by being composed of a single 4-axis handle and having a built-in control box to receive commands. Using this interface, aircraft control becomes easier, and a co-pilot or a less qualified operator can take control even when the pilot station is unavailable (e.g., failure, pilot issue).

[0039] The 4-axis stick can be located on the outer side of the aircraft to facilitate the integration of other equipment into the center console.

[0040] According to one possibility compatible with the previously described possibility, the control system may include a processing subassembly that determines at least one position set value to be reached on at least one aerodynamic control surface as a function of at least one command, and the control system includes at least one operating subassembly configured to generate at least one operating set value transmitted to at least one actuator to control the aerodynamic control surface as a function of said position set value, and said processing subassembly is connected to a first connector assembly and a second connector assembly and is configured to determine a current configuration as a function of information received by each connector of the first connector assembly and the second connector assembly.

[0041] The processing subassembly can determine in the conventional way which control member is connected to which connector by a standard addressing method.

[0042] The processing subassembly may be configured to select control laws to be applied as a function of the current configuration, or even the set of human-machine interfaces transmitting the command. For example, in an intermediate configuration, the processing subassembly may apply a first set of stored laws when a control member of a complete set of human-machine interfaces issues a command, and apply a second set of stored laws when a single control member of a simplified set of human-machine interfaces issues a command.

[0043] According to one possibility compatible with the prior possibilities, the rotary-wing aircraft may include a display, and the control system is configured to transmit at least one carrier signal of the current configuration directly or indirectly to the display, and the display displays at least one carrier symbol of the current configuration.

[0044] This allows the crew to visually check the aircraft's configuration.

[0045] According to one possibility compatible with the previously described possibility, in a two-pilot configuration, each complete human-machine interface set may include a switch, which inhibits the operation of the complete human-machine interface set when the switch is activated.

[0046] Therefore, the operation of a complete set of human-machine interfaces can be manualized without changing the configuration.

[0047] According to one possibility compatible with the previously described possibility, in a two-pilot configuration, two control members performing the same function in each of the two complete sets of human-machine interfaces may be passive members that return to a predetermined position when no force is applied, and the control system is configured to prohibit the operation of one of the two control members when the two control members operate simultaneously.

[0048] When the control member is not operating, it returns to the reference position. To facilitate changes between configurations, this feature eliminates the need to place a mechanical device between the control members of two sets of human-machine interfaces.

[0049] Alternatively, in a two-pilot configuration, two control members performing the same function of each of the two complete sets of human-machine interfaces may be active members, and when one of the two control members moves, the control system may be configured to transmit a signal to the other control member to control the same movement.

[0050] Using two sets of active, complete human-machine interfaces facilitates changes between configurations, and this feature prevents the placement of mechanical devices between the control members of the two sets of human-machine interfaces.

[0051] According to one possibility compatible with the previous possibility, the first connector assembly and the second connector assembly are arranged transversely on both sides of a vertical plane extending from the nose to the tail of a rotary-wing aircraft.

[0052] In conventional rotary-wing aircraft, the first connector assembly and the second connector assembly are positioned, for example, to the left and right of the cockpit, depending on the aircraft's direction of movement.

[0053] The present invention also relates to a method implemented by such a rotary-wing aircraft.

[0054] Accordingly, the present invention relates to a method for controlling a rotary-wing aircraft comprising an electric flight control system, wherein the electric flight control system comprises a control system for controlling at least one aerodynamic control surface as a function of at least one command.

[0055] The electric flight control system includes a first connector assembly and a second connector assembly connected to the control system by at least one wired link, and the method comprises,

[0056] ― connecting a single set of human-machine interfaces to the first connector assembly or the second connector assembly, or connecting two sets of human-machine interfaces to the first connector assembly and the second connector assembly, respectively; and

[0057] ― During the initialization phase, the control system is used to identify the current configuration from a plurality of reference configurations by communicating with the first connector assembly and the second connector assembly, and

[0058] The above plurality of standard configurations are,

[0059] ― A two-pilot configuration in which two identical and complete sets of human-machine interfaces are connected to a first connector assembly and a second connector assembly, respectively; and

[0060] ― A single complete set of human-machine interfaces includes at least one simplified configuration connected to one of the first connector assembly and the second connector assembly.

[0061] The above at least one simplified configuration may include a rigid single pilot configuration comprising a single complete set of human-machine interfaces connected to a first connector assembly or a second connector assembly.

[0062] The above at least one simplified configuration may include a complete human-machine interface set connected to one of the first connector assembly and the second connector assembly, and an intermediate configuration having a simplified human-machine interface set connected to the first connector assembly or the second connector assembly, which is not connected to the complete human-machine interface set. Brief explanation of the drawing

[0063] The present invention and its advantages are further explained in detail from the following description of exemplary examples provided with reference to the accompanying drawings. FIG. 1 is a diagram illustrating a rotary-wing aircraft according to the present invention. FIG. 2 is a diagram illustrating a flight control system with a two-pilot configuration according to the present invention. FIG. 3 is a diagram illustrating an intermediate flight control system according to the present invention. FIG. 4 is a diagram illustrating a flight control system with a strict one-person pilot configuration according to the present invention. FIG. 5 is a diagram illustrating the method of the present invention. Specific details for implementing the invention

[0064] Elements existing in two or more drawings are assigned the same reference numeral in each drawing.

[0065] FIG. 1 shows a plan view of a rotary-wing aircraft (1) according to the present invention.

[0066] A rotary-wing aircraft (1) has an airframe (2) that extends from the nose (3) to the tail (4) along a vertical plane (100) from the front to the rear. The rotary-wing aircraft (1) additionally includes a cockpit (5) in the airframe (2). For example, the cockpit (5) accommodates at least one dashboard (6) and / or center console (7).

[0067] In particular, the cockpit (5) may include two stations (8, 9), each station may form a cockpit. According to the illustrated example, the two stations (8, 9) are located on both sides of the vertical plane (100) and on both sides of the central console (7).

[0068] Furthermore, the rotary-wing aircraft (1) includes at least one movable aerodynamic control surface (11) for controlling the movement of the rotary-wing aircraft (1). This aerodynamic control surface (11) may take the form of a blade, a flap, etc.

[0069] For example, a rotary-wing aircraft (1) includes a main rotor (98), which can contribute to at least the lift of the rotary-wing aircraft (1). The main rotor (98) includes at least one blade (12) forming an aerodynamic control surface (11) and is illustrated by a dashed line.

[0070] Additionally, the rotary-wing aircraft (1) may include an auxiliary rotor (99), which may contribute to controlling the yaw motion of at least the rotary-wing aircraft (1). The auxiliary rotor (99) includes at least one blade (13) that forms an aerodynamic control surface (11). According to the illustrated example, the auxiliary rotor (99) may be a tail rotor located at the tail section (4) of the rotary-wing aircraft (1). According to another example, the auxiliary rotor (99) may be in the form of a propeller.

[0071] Independent of these embodiments, the rotary-wing aircraft (1) includes an electric flight control system (10). This electric flight control system (10) includes a control system (70) for controlling at least one aerodynamic control surface (11) as a function of at least one control command, more simply called a “command”.

[0072] The electric flight control system (10) includes a first connector assembly (20) and a second connector assembly (25) connected to the control system (70), for example, via one or more electric and / or optical wired links. The first connector assembly (20) and the second connector assembly (25) are optionally positioned laterally on both sides of the vertical plane (100) or even symmetrical with respect to each other.

[0073] According to the example of FIG. 2, each connector assembly (20, 25) may include three subassemblies intended for three control members, and each subassembly may include one or more connectors. For simplification and to avoid complexity, the first connector assembly (20) may include three subassemblies each having at least one connector (21, 22, 23), and the second connector assembly (25) may include three subassemblies each having at least one connector (26, 27, 28). For example, the connectors (21, 22, 23, 26, 27, 28) are identical.

[0074] Each connector assembly (20, 25) has the function of acquiring at least one command, for example in the form of an electrical or optical command signal, and transmitting it to a control system (70). The control system (70) is configured to control one or more aerodynamic control surfaces (11) as a function of one or more commands.

[0075] For example, the control system (70) includes a processing subassembly (75) that determines at least one position setting value to be reached by at least one aerodynamic control surface (11) as a function of at least one command. Conventionally, the processing subassembly (75) may include one or more computers (76).

[0076] The term "computer" refers to a processing unit capable of performing digital processing, along with other forms of integrated circuits containing processors or logic circuits. A processing unit may perform analog processing using analog components, whether or not integrated into the integrated circuit, such as operational amplifiers, for example. The term "processor" may refer synonymously to a central processing unit or CPU, a graphics processing unit or GPU, a digital signal processor or DSP, a microcontroller, etc.

[0077] Additionally, the control system (70) includes at least one operating subassembly (80), and the operating subassembly (80) is configured to generate at least one operating set value as a function of a position set value, and the operating set value is transmitted to at least one actuator (90) to control the aerodynamic control surface (11) directly or indirectly through a mechanical drive chain.

[0078] Accordingly, the processing subassembly (75) is connected to each connector (21-23, 24-26) of the first connector assembly (20) and the second connector assembly (25) by one or more wire links exemplified by a continuous line. As a function of a received command, the processing subassembly (75) transmits a position setting value as a function of at least one stored rule via the wire link to at least one operating subassembly (80), which controls at least one actuator (90).

[0079] According to the example illustrated, the pitch of the blades (12) of the main rotor (98) can be changed by at least three servo control units (91, 92, 93) articulated to a swashplate system (14) connected to each blade (12) by at least one pitch change rod. According to this same example, the pitch of the blades (13) of the auxiliary rotor (99) can be changed by at least one actuator (89).

[0080] To generate commands, for each flight, the rotary-wing aircraft (1) includes at least one set of human-machine interfaces (40) reversibly connected to a first connector assembly (20) or a second connector assembly (25).

[0081] Each human-machine interface set (40) includes at least one control member (50) equipped with a control box (51). Reference numeral 50 indicates any control member, and reference numeral 51 indicates any control box.

[0082] The control box (51) of the control member (50) is connected to at least one connector (21-23, 24-26) of the connector subassembly by at least one wired link. The control box (51) of the control member (50) is configured to generate the command as a result of an operation on the control member (50), that is, as a result of the movement of the control member or the button operation of the control member.

[0083] In particular, the rotary-wing aircraft (1) is in a current configuration selected from a plurality of reference configurations (CONF1, CONF2, CONF3) during each flight. The reference configurations include a two-pilot configuration (CONF1) and at least one simplified configuration, which is a strict single-pilot or intermediate configuration.

[0084] According to the control system (70) and the illustrated example, the processing subassembly (75) is configured to determine the current configuration as a function of information received from a control member, or from a member connected through each connector of the first connector assembly (20) and the second connector assembly (25). Additionally, according to the control system (70) and the illustrated example, the processing subassembly (75) is configured to control one or more actuators (90) accordingly.

[0085] Optionally, the rotary-wing aircraft (1) may include a display (95) that is controlled directly or indirectly by a control system (70). According to the control system (70) and the illustrated example, the processing subassembly (75) is configured to transmit at least one carrier signal of the current configuration directly or indirectly to the display (95) through the avionics system of the rotary-wing aircraft (1). Then, the display (95) displays at least one symbol (96) representing the current configuration. According to the illustrated example, the symbol (96) may take the form of a series of characters representing the current configuration.

[0086] FIG. 2 illustrates a two-person pilot configuration (CONF1) in which two identical sets of human-machine interfaces, referred to as complete sets of human-machine interfaces (45), are each connected directly or indirectly through at least one adapter link. FIG. 1 illustrates a connector subassembly each having a single connector and a control member connected to the single connector. According to another possibility, each connector assembly (20) may include at least one connector subassembly having at least two connectors, and the control member may be connected to multiple connectors of the same connector subassembly. Furthermore, the connector may be connected to only one control member.

[0087] The expression “complete set of human-machine interfaces (45)” is, for example

[0088] ― A first control member (56) for controlling the pitch of the blade (12) of the main rotor (98), such as a general cyclic stick;

[0089] ― A second control member (58) for controlling the pitch of the blade (12) of the main rotor (98) differently from the first control member (56); and

[0090] — It means an interface set including a third control member (57), such as a rudder bar, for controlling the pitch of the blade (13) of the auxiliary rotor (99).

[0091] FIG. 1 illustrates a control member connected to a single connector, but one or more interfaces may be connected to multiple connectors of a subassembly of the same connector. For example, a second connector assembly (25) may include a subassembly having multiple connectors (26), and a first connector assembly (20) may include a subassembly having multiple connectors (23) instead of the single connector (23) and single connector (26) shown in the example of FIG. 2. Here, a first control member (56) of one complete human-machine interface set may be connected to multiple connectors (26), and a first control member (56) of another complete human-machine interface set may be connected to multiple connectors (23).

[0092] In a two-pilot configuration (CONF1), each complete human-machine interface set (45) may be equipped with a switch (94) that prohibits the operation of the corresponding complete human-machine interface set (45) when this switch (94) is activated.

[0093] For example, a switch (94) is mounted by a control member (50) and connected to a control box (51) of the control member (50). When the switch (94) is activated, the associated control box (51) transmits a signal to the control system (70) indicating that the entire set of human-machine interfaces (45) should be ignored.

[0094] In a two-pilot configuration (CONF1), at least two control members (56; 57; 58) that effectively perform the same function are each mounted on two complete human-machine interface sets (45). Thus, the two complete human-machine interface sets (45) of FIG. 2 have two identical first control members (56), two identical second control members (58), and two identical third control members (57).

[0095] Optionally, two identical control members (50) of the two complete sets of human-machine interfaces (45) are manual members that return to a predetermined position when no force is applied. Furthermore, the control system (70) is configured to disable one of the two control members (56; 57; 58), that is, to ignore the operation of both control members (56; 57; 58) simultaneously.

[0096] Optionally, two identical control members (50) of the two complete sets of human-machine interfaces (45) are active members, that is, at least one active device, such as a cylinder or motor capable of applying force to each control member (50), is provided. Thus, when one of the two control members (56; 57; 58) moves, the control system (70), and, for example, the processing subassembly (75), is configured to transmit a signal to the other control member (56; 57; 58) to command the same movement.

[0097] Furthermore, in a simplified configuration (CONF2, CONF3), a single complete human-machine interface set (45) is connected to the first connector assembly (20) or the second connector assembly (25).

[0098] FIG. 3 illustrates a simplified configuration in the form of an intermediate configuration (CONF2). In this intermediate configuration (CONF2), the rotary-wing aircraft (1) includes a complete human-machine interface set (45) connected to one of the first connector assembly (20) and the second connector assembly (25), and a simplified human-machine interface set (46) connected to the other connector assembly (20, 25). The simplified human-machine interface set (46) includes, for example, only one control member (59) capable of controlling the rotary-wing aircraft (1) along four axes.

[0099] Accordingly, the control system (70), in particular the processing subassembly (75), applies at least one first law to generate a set value when one of the control members (50) of the complete human-machine interface set (45) is operated, and applies at least one second law when a single control member (59) of the simplified human-machine interface set (46) is operated.

[0100] Figure 4 illustrates a simplified configuration in the form of a strict single pilot configuration (CONF3).

[0101] In this strict single pilot configuration (CONF3), the rotary-wing aircraft (1) includes only one complete set of human-machine interfaces (45) connected directly or indirectly to the first connector assembly (20) or the second connector assembly (25) via at least one adapter link.

[0102] Under these conditions, FIG. 5 illustrates a method of controlling such a rotary-wing aircraft (1).

[0103] This method includes the step of connecting at least one set of human-machine interfaces to one of the first connector assembly (20) and the second connector assembly (25) during step (STP1). The operator connects at least one set of human-machine interfaces (45) to place the rotary-wing aircraft in one of the aforementioned reference configurations.

[0104] Next, this method includes a step of identifying the current configuration using, for example, an existing addressing method, during the initialization step (PINI) and using the control system (70) during the step (STP2).

[0105] This method includes the step of controlling a rotary-wing aircraft (1) by controlling the movement of at least one aerodynamic control surface (11) together with a control system (70) as a function of the action of a control member (50).

[0106] Naturally, the present invention may be subject to numerous variations depending on its implementation. While there are various embodiments described above, it should be readily understood that it is impossible to fully identify all possible embodiments. Of course, the described means may be replaced with equivalent means without departing from the scope of the invention and claims. Explanation of the symbols

[0107] 1: Aircraft 2: Aircraft 3: Standard Bearer 4: Tail 5: Cockpit 6: Dashboard 7: Center console 8, 9: Station 10: Electric Flight Control System 11: Aerodynamic control surfaces 12, 13: Blade 14: Swashplate 20: First connector assembly 21, 22, 23, 24, 26, 27, 28: Connector 25: Second connector assembly 40, 45: Human-Machine Interface Set 50, 59: Control element 51: Control box 56: First control member 57: Third control element 58: Second control element 70: Control System 75: Processing subassembly 76: Computer 80: Operational subassembly 89, 90: Actuator 91, 92, 93: Servo control unit 94: Switch 98: Main rotor 99: Auxiliary Rotor 100: Vertical plane CONF1, CONF2, CONF3: Standard configuration PiNi: Initialization Phase

Claims

Claim 1 A rotary-wing aircraft (1) comprising an electric flight control system (10) having a control system (70) for controlling at least one aerodynamic control surface (11) as a function of at least one command, wherein the electric flight control system (10) comprises a first connector assembly (20) and a second connector assembly (25) connected to the control system (70) by at least one wired link, and at least one human-machine interface set (40) is reversibly connected to the first connector assembly or the second connector assembly, and the human-machine interface set (40) comprises at least one control member (50) having a control box (51) configured to generate a command according to the operation of the control member (50); and the rotary-wing aircraft (1) has a current configuration selected from a plurality of reference configurations (CONF1, CONF2, CONF3) during each flight; The control system determines a current configuration among reference configurations (CONF1, CONF2, CONF3) by communicating through a first connector assembly (20) and a second connector assembly (25) during an initialization phase (PINI), wherein the plurality of reference configurations include: a two-pilot configuration (CONF1) in which two identical and complete human-machine interface sets (45) are respectively connected to the first connector assembly (20) and the second connector assembly (25); and at least one simplified configuration (CONF2, CONF3) in which a single complete human-machine interface set (45) is connected to one of the first connector assembly (20) and the second connector assembly (25), a rotary-wing aircraft (1). Claim 2 A rotary-wing aircraft (1), characterized in that, in claim 1, one or more complete human-machine interface sets (45) each include a first control member (56) for controlling the pitch of the blades of the main rotor (98), a second control member (58) for controlling the pitch of the blades of the main rotor (98) differently from the first control member (56), and a third control member (57) for controlling the pitch of the blades of the auxiliary rotor (99). Claim 3 A rotary-wing aircraft (1), characterized in that, in claim 1, the simplified configuration(s) include a rigid single pilot configuration (CONF3) having a single complete human-machine interface set (45) connected to the first connector assembly (20) or the second connector assembly (25). Claim 4 A rotary-wing aircraft (1), wherein the simplified configuration(s) comprises an intermediate configuration (CONF2) having a complete human-machine interface set (45) connected to one of the first connector assembly (20) and the second connector assembly (25), and a simplified human-machine interface set (46) connected to the first connector assembly (20) or the second connector assembly (25) that is not connected to the complete human-machine interface set (45). Claim 5 In paragraph 4, the rotary-wing aircraft (1) is characterized in that the simplified human-machine interface set (46) comprises only one control member (59). Claim 6 In claim 1, the control system (70) comprises a processing subassembly (75) that determines at least one position setting value to be reached by at least one aerodynamic control surface (11) as a function of at least one command, and the control system comprises at least one operating subassembly (80) configured to generate at least one operating setting value transmitted to at least one actuator (90) to control the aerodynamic control surface (11) as a function of the position setting value, and the processing subassembly (75) is connected to a first connector assembly (20) and a second connector assembly (25) and is configured to determine a current configuration as a function of information received by each connector of the first connector assembly (20) and the second connector assembly (25), characterized in that the rotary-wing aircraft (1). Claim 7 In claim 1, the rotary-wing aircraft (1) comprises a display (95), and the control system (70) is configured to transmit at least one carrier signal of the current configuration directly or indirectly to the display (95), and the display (95) displays at least one carrier symbol (96) of the current configuration, characterized in that the rotary-wing aircraft (1). Claim 8 A rotary-wing aircraft (1) according to claim 1, wherein in the two-pilot configuration (CONF1), each complete human-machine interface set (45) includes a switch (94), and when the switch (94) is activated, the switch (94) prohibits the operation of the complete human-machine interface set (45). Claim 9 A rotary-wing aircraft (1) according to claim 1, wherein in the two-pilot configuration (CONF1), two control members (56; 57; 58) each performing the same function of two complete human-machine interface sets (45) are passive members that return to a predetermined position when no force is applied, and the control system (70) is configured to prohibit the operation of one of the two control members (56; 57; 58) when the two control members (56; 57; 58) operate simultaneously. Claim 10 A rotary-wing aircraft (1), characterized in that, in the two-pilot configuration (CONF1), two control members (56; 57; 58) each performing the same function of two complete human-machine interface sets (45) are active members; and when one of the two control members (56; 57; 58) moves, the control system (70) is configured to transmit a signal to the other control member to control the same movement. Claim 11 A rotary-wing aircraft (1), characterized in that, in claim 1, the first connector assembly (20) and the second connector assembly (25) are arranged transversely on both sides of a vertical plane (100) extending from the nose (3) to the tail (4) of the rotary-wing aircraft (1). Claim 12 A rotary-wing aircraft (1), wherein, in claim 1, the control box (51) is connected to at least one connector (21-23, 24-26) of the first connector assembly or the second connector assembly by at least one wired link, and the connector has the function of acquiring command(s) and transmitting them to a control system (70). Claim 13 A method for controlling a rotary-wing aircraft (1) comprising an electric flight control system (10), wherein the electric flight control system (10) comprises a control system (70) for controlling at least one aerodynamic control surface (11) as a function of at least one command, and wherein the electric flight control system (10) comprises a first connector assembly (20) and a second connector assembly (25) connected to the control system (70) by at least one wired link, and the method comprises the step (STP1) of connecting a single set of human-machine interfaces to the first connector assembly (20) or the second connector assembly (25), or connecting two sets of human-machine interfaces to the first connector assembly (20) and the second connector assembly (25), respectively; A method for controlling a rotary-wing aircraft (1), comprising: a step (STP2) of identifying a current configuration among a plurality of reference configurations by communicating with a first connector assembly (20) and a second connector assembly (25) using the control system (70) during an initialization step (PINI); wherein the plurality of reference configurations include: a two-pilot configuration (CONF1) in which two identical and complete sets of human-machine interfaces are connected to the first connector assembly and the second connector assembly, respectively; and at least one simplified configuration (CONF2, CONF3) in which a single complete set of human-machine interfaces is connected to one of the first connector assembly (20) and the second connector assembly (25). Claim 14 A method for controlling a rotary-wing aircraft (1), wherein, in the 13th, the simplified configuration(s) include a rigid single pilot configuration (CONF3) having only one complete human-machine interface set (45) connected to the first connector assembly (20) or the second connector assembly (25). Claim 15 A method for controlling a rotary-wing aircraft (1), wherein, in the 13th, the simplified configuration(s) include an intermediate configuration (CONF2) having a complete set of human-machine interfaces connected to one of the first connector assembly (20) and the second connector assembly (25), and a simplified set of human-machine interfaces (46) connected to the first connector assembly (20) or the second connector assembly (25) which is not connected to the complete set of human-machine interfaces (45).

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