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A device (10) for assisted piloting of an aircraft having a rotary wing with a plurality of second blades (3′) and a propulsion unit with a plurality of first blades (2′). The device includes control means (30, 40) for delivering a movement order (O) for moving in a direction, said device (10) havin

A device (10) for assisted piloting of an aircraft having a rotary wing with a plurality of second blades (3′) and a propulsion unit with a plurality of first blades (2′). The device includes control means (30, 40) for delivering a movement order (O) for moving in a direction, said device (10) having a processor unit (20) for transforming said order (O) into an acceleration setpoint (C) along said direction, and then for transforming said acceleration setpoint (C) into at least one required longitudinal attitude setpoint (θ*) that is transmitted to a first automatic system (26) for maintaining longitudinal attitude by controlling a longitudinal cyclic pitch of the second blades (3′), and into a first required load factor setpoint (Nx*) in a longitudinal direction that is transmitted to a second automatic system (25) for maintaining load factor by controlling the collective pitch of the first blades.

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1. A method of assisted piloting for an aircraft having a rotary wing and a propulsion unit including at least one propulsion propeller, each propeller having a plurality of first blades, and the rotary wing including a rotor provided with a plurality of second blades, the method comprising: transla

1. A method of assisted piloting for an aircraft having a rotary wing and a propulsion unit including at least one propulsion propeller, each propeller having a plurality of first blades, and the rotary wing including a rotor provided with a plurality of second blades, the method comprising: translating an order given to an aircraft controller by a pilot of the aircraft to request a movement in a direction into an acceleration setpoint along said direction;transforming, by a processor in communication with the aircraft controller, the acceleration setpoint by predetermined relationships into a required longitudinal attitude setpoint (θ*) and into a first required load factor setpoint (Nx*) in a longitudinal direction of the aircraft parallel to a roll axis of said aircraft;transmitting the required longitudinal attitude setpoint (θ*) to a first automatic system for maintaining longitudinal attitude by controlling a longitudinal cyclic pitch of the second blades of the rotary wing in order to comply with said required longitudinal attitude setpoint (θ*); andtransmitting the first required load factor setpoint (Nx*) to a second automatic system for maintaining load factor by controlling a collective pitch of the first blades of the propulsion unit in order to comply with said first load factor setpoint (Nx*). 2. The method according to claim 1, wherein when said order is an order to move in a longitudinal direction of the aircraft parallel to a roll axis of said aircraft, said order to move in a longitudinal direction is translated into a longitudinal acceleration setpoint, and then the longitudinal acceleration setpoint is transformed by predetermined relationships solely into the required longitudinal attitude setpoint (θ*) transmitted to the first automatic system for maintaining longitudinal attitude and into the first required load factor setpoint (Nx*) transmitted to the second automatic system for maintaining load factor. 3. A method of assisted piloting for an aircraft having a rotary wing and a propulsion unit including at least one propulsion propeller, each propeller having a plurality of first blades, and the rotary wing including a rotor provided with a plurality of second blades, the method comprising: translating an order to an aircraft controller given by a pilot of the aircraft to request a movement in a direction into an acceleration setpoint along said direction;transforming, by a processor in communication with the aircraft controller, the acceleration setpoint by predetermined relationships into a required longitudinal attitude setpoint (θ*) and into a first required load factor setpoint (Nx*) in a longitudinal direction of the aircraft parallel to a roll axis of said aircraft;transmitting the required longitudinal attitude setpoint (θ*) to a first automatic system for maintaining longitudinal attitude by controlling a longitudinal cyclic pitch of the second blades of the rotary wing in order to comply with said required longitudinal attitude setpoint (θ*); andtransmitting the first required load factor setpoint (Nx*) to a second automatic system for maintaining load factor by controlling a collective pitch of the first blades of the propulsion unit in order to comply with said first load factor setpoint (Nx*);wherein when said order is an order to move in a longitudinal direction of the aircraft parallel to a roll axis of said aircraft, said order to move in a longitudinal direction is translated into a longitudinal acceleration setpoint, and then the longitudinal acceleration setpoint is transformed by predetermined relationships solely into the required longitudinal attitude setpoint (θ*) transmitted to the first automatic system for maintaining longitudinal attitude and into the first required load factor setpoint (Nx*) transmitted to the second automatic system for maintaining load factor;wherein said required longitudinal attitude setpoint (θ*) is determined by the following first longitudinal control relationship: θ*=(180/Pi)×[(−a)×(γx*/g)−k]/(a+b) where “θ*” represents the required longitudinal attitude setpoint expressed in degrees, “Pi” represents the number π, “γx*” represents the longitudinal acceleration setpoint, “g” represents the acceleration due to gravity, “×” represents the multiplication sign, “/” represents the division sign, “a” represents a first longitudinal constant, “b” represents a second longitudinal constant, and “k” represents a third longitudinal constant. 4. A method of assisted piloting for an aircraft having a rotary wing and a propulsion unit including at least one propulsion propeller, each propeller having a plurality of first blades, and the rotary wing including a rotor provided with a plurality of second blades, the method comprising: translating an order given to an aircraft controller by a pilot of the aircraft to request a movement in a direction into an acceleration setpoint along said direction;transforming, by a processor in communication with the aircraft controller, the acceleration setpoint by predetermined relationships into a required longitudinal attitude setpoint (θ*) and into a first required load factor setpoint (Nx*) in a longitudinal direction of the aircraft parallel to a roll axis of said aircraft;transmitting the required longitudinal attitude setpoint (θ*) to a first automatic system for maintaining longitudinal attitude by controlling a longitudinal cyclic pitch of the second blades of the rotary wing in order to comply with said required longitudinal attitude setpoint (θ*); andtransmitting the first required load factor setpoint (Nx*) to a second automatic system for maintaining load factor by controlling a collective pitch of the first blades of the propulsion unit in order to comply with said load factor setpoint (Nx*);wherein when said order is an order to move in a longitudinal direction of the aircraft parallel to a roll axis of said aircraft, said order to move in a longitudinal direction is translated into a longitudinal acceleration setpoint, and then the longitudinal acceleration setpoint is transformed by predetermined relationships solely into the required longitudinal attitude setpoint (θ*) transmitted to the first automatic system for maintaining longitudinal attitude and into the first required load factor setpoint (Nx*) transmitted to the second automatic system for maintaining load factor;wherein said first required load factor setpoint (Nx*) is determined by the following second longitudinal control relationship: Nx*=[b×(γx*/g)−k]/(a+b) where “Nx*” represents said first required load factor setpoint, “γx*” represents the longitudinal acceleration setpoint, “g” represents the acceleration due to gravity, “×” represents the multiplication sign, “/” represents the division sign, “a” represents a first longitudinal constant, “b” represents a second longitudinal constant, and “k” represents a third longitudinal constant. 5. The method according to claim 1, wherein the required longitudinal attitude setpoint (θ*) is modified by incrementing or decrementing by means of an attitude adjustment member when the acceleration setpoint is zero. 6. The method according to claim 3, wherein the third longitudinal constant (k) is equal to zero in order to reset to zero said first required load factor setpoint (Nx*) when the pilot does not give an order to move in said longitudinal direction, said longitudinal acceleration setpoint being zero. 7. The method according to claim 3, wherein the third longitudinal constant “k” is determined by the following formula: k=−sin(θequi)×(a+b) where “×” represents the multiplication sign, “a” represents said first longitudinal constant, “b” represents said second longitudinal constant, and “θequi” represents a predetermined equilibrium setpoint optimizing the performance of the aircraft in predetermined stabilized flight stages, the longitudinal acceleration setpoint (γx*) being zero. 8. The method according to claim 2, wherein when the pilot does not give an order to move in the longitudinal direction, the first load factor setpoint (Nx*) is equal to the sine of the current longitudinal attitude (θ), the longitudinal acceleration setpoint (γx*) being zero. 9. The method according to claim 3, wherein said longitudinal constants (a, b, k) are selected from a list including at least one of the following combinations: a first longitudinal combination in which the first longitudinal setpoint is equal to “1”, the second longitudinal constant is equal to zero, and the third longitudinal constant is equal to zero;a second longitudinal combination in which the first longitudinal setpoint is equal to “0.001”, the second longitudinal constant is equal to “1”, and the third longitudinal constant is equal to zero; anda third longitudinal combination in which the first longitudinal setpoint is equal to “0.9”, the second longitudinal constant is equal to “2”, and the third longitudinal constant is equal to zero. 10. The method according to claim 1, wherein, when said order (O) is an order to move in a vertical direction parallel to the gravity direction, this movement order is translated along an elevation direction into a vertical acceleration setpoint, and then this vertical acceleration setpoint is transformed into the required longitudinal attitude setpoint (θ*) that is transmitted to the first automatic system for maintaining longitudinal attitude, into the first load factor setpoint (Nx*) that is transmitted to the second automatic system for maintaining load factor, and into a second load factor setpoint (NZcoll*) that is transmitted to a third automatic system for maintaining load factor by controlling collective pitch variation of the second blades of the rotary wing. 11. A method of assisted piloting for an aircraft having a rotary wing and a propulsion unit including at least one propulsion propeller, each propeller having a plurality of first blades, and the rotary wing including a rotor provided with a plurality of second blades, the method comprising: translating an order given to an aircraft controller by a pilot of the aircraft to request a movement in a direction into an acceleration setpoint along said direction;transforming, by a processor in communication with the aircraft controller, the acceleration setpoint by predetermined relationships into a required longitudinal attitude setpoint (θ*) and into a first required load factor setpoint (Nx*) in a longitudinal direction of the aircraft parallel to a roll axis of said aircraft;transmitting the required longitudinal attitude setpoint (θ*) to a first automatic system for maintaining longitudinal attitude by controlling a longitudinal cyclic pitch of the second blades of the rotary wing in order to comply with said required longitudinal attitude setpoint (θ*); andtransmitting the first required load factor setpoint (Nx*) to a second automatic system for maintaining load factor by controlling a collective pitch of the first blades of the propulsion unit in order to comply with said first load factor setpoint (Nx*);wherein, when said order (O) is an order to move in a vertical direction parallel to the gravity direction, this movement order is translated along an elevation direction into a vertical acceleration setpoint, and then this vertical acceleration setpoint is transformed into the required longitudinal attitude setpoint (θ*) that is transmitted to the first automatic system for maintaining longitudinal attitude, into the first load factor setpoint (Nx*) that is transmitted to the second automatic system for maintaining load factor, and into a second load factor setpoint (NZcoll*) that is transmitted to a third automatic system for maintaining load factor by controlling collective pitch variation of the second blades of the rotary wing;wherein said required longitudinal attitude setpoint is determined by the following first vertical control relationship: θ*=∫q*dt with:q*=(g/u)×[−a″×(Nz*+cos θ×cos φ)−k″]/(a″+b″)and:Nz*=(1/(a′×cos θ×cos φ+b′×sin θ))×(−a′×(Γz*/g+1)−k′×sin θ) where “θ*” represents the required longitudinal attitude setpoint expressed in radians, “Γz*” represents the vertical acceleration setpoint, “g” represents the acceleration due to gravity, “u” represents the current longitudinal speed of the aircraft, “θ” represents the current longitudinal attitude, “φ” represents the current roll angle of the aircraft, “×” represents the multiplication sign, “/” represents the division sign, “a′” represents a first vertical constant, “b′” represents a second vertical constant, “k′” represents a third vertical constant, “a″” represents a fourth vertical constant, “b″” represents a fifth vertical constant, and “k″” represents a sixth vertical constant, the required longitudinal attitude setpoint θ* being frozen when the vertical acceleration setpoint is equal to 1. 12. A method of assisted piloting for an aircraft having a rotary wing and a propulsion unit including at least one propulsion propeller, each propeller having a plurality of first blades, and the rotary wing including a rotor provided with a plurality of second blades, the method comprising: translating an order given to an aircraft controller by a pilot of the aircraft to request a movement in a direction into an acceleration setpoint along said direction;transforming, by a processor in communication with the aircraft controller, the acceleration setpoint by predetermined relationships into a required longitudinal attitude setpoint (θ*) and into a first required load factor setpoint (Nx*) in a longitudinal direction of the aircraft parallel to a roll axis of said aircraft;transmitting the required longitudinal attitude setpoint (θ*) to a first automatic system for maintaining longitudinal attitude by controlling a longitudinal cyclic pitch of the second blades of the rotary wing in order to comply with said required longitudinal attitude setpoint (θ*); andtransmitting the first required load factor setpoint (Nx*) to a second automatic system for maintaining load factor by controlling a collective pitch of the first blades of the propulsion unit in order to comply with said first load factor setpoint (Nx*);wherein, when said order (O) is an order to move in a vertical direction parallel to the gravity direction, this movement order is translated along an elevation direction into a vertical acceleration setpoint, and then this vertical acceleration setpoint is transformed into the required longitudinal attitude setpoint (θ*) that is transmitted to the first automatic system for maintaining longitudinal attitude, into the first load factor setpoint (Nx*) that is transmitted to the second automatic system for maintaining load factor, and into a second load factor setpoint (NZcoll*) that is transmitted to a third automatic system for maintaining load factor by controlling collective pitch variation of the second blades of the rotary wing;wherein said first load factor setpoint (Nx*) is determined by the following second vertical control relationship: Nx*=(1/(a′×cos θ×cos φ+b′×sin θ))×(b′×(Γz*/g+1)−k′×cos θ×cos φ) where “Nx*” represents the first required load factor setpoint, “Γz*” represents the vertical acceleration setpoint, “g” represents the acceleration due to gravity, “×” represents the multiplication sign, “/” represents the division sign, “θ” represents the current longitudinal attitude, “φ” represents the current roll angle of the aircraft, “a′” represents a first vertical constant, “b′” represents a second vertical constant, “k′” represents a third vertical constant, in the absence of said order to move in a vertical direction, said first setpoint Nx* being equal to the sine of the current longitudinal attitude (θ). 13. A method of assisted piloting for an aircraft having a rotary wing and a propulsion unit including at least one propulsion propeller, each propeller having a plurality of first blades, and the rotary wing including a rotor provided with a plurality of second blades, the method comprising: translating an order given to an aircraft controller by a pilot of the aircraft to request a movement in a direction into an acceleration setpoint along said direction;transforming, by a processor in communication with the aircraft controller, the acceleration setpoint by predetermined relationships into a required longitudinal attitude setpoint (θ*) and into a first required load factor setpoint (Nx*) in a longitudinal direction of the aircraft parallel to a roll axis of said aircraft;transmitting the required longitudinal attitude setpoint (θ*) to a first automatic system for maintaining longitudinal attitude by controlling a longitudinal cyclic pitch of the second blades of the rotary wing in order to comply with said required longitudinal attitude setpoint (θ*); andtransmitting the first required load factor setpoint (Nx*) to a second automatic system for maintaining load factor by controlling a collective pitch of the first blades of the propulsion unit in order to comply with said first load factor setpoint (Nx*);wherein, when said order (O) is an order to move in a vertical direction parallel to the gravity direction, this movement order is translated along an elevation direction into a vertical acceleration setpoint, and then this vertical acceleration setpoint is transformed into the required longitudinal attitude setpoint (θ*) that is transmitted to the first automatic system for maintaining longitudinal attitude, into the first load factor setpoint (Nx*) that is transmitted to the second automatic system for maintaining load factor, and into a second load factor setpoint (NZcoll*) that is transmitted to a third automatic system for maintaining load factor by controlling collective pitch variation of the second blades of the rotary wing;wherein said second load factor setpoint (NZcoll*) is determined by the following third vertical control relationship: NZcoll*=(b″×(Nz*+cos θ×cos φ)−k″)/(a″+b″) andNz*=1/(a′×cos θ×cos φ+b′×sin θ))×(−a′×(Γz*/g+1)−k′×sin θ) where “NZcoll” represents the second required load factor setpoint, “Γz*” represents the vertical acceleration setpoint, “g” represents the acceleration due to gravity, “θ” represents the current longitudinal attitude, “φ” represents the current roll angle of the aircraft, “×” represents the multiplication sign, “/” represents the division sign, “a′” represents a first vertical constant, “b′” represents a second vertical constant, “k′” represents a third vertical constant, “a″” represents a fourth vertical constant, “b″” represents a fifth vertical constant, and “k″” represents a sixth vertical constant. 14. The method according to claim 11, wherein said vertical constants are selected from a list including at least one of the following combinations: a first vertical combination in which the first vertical constant is equal to “1”, the second vertical constant is equal to zero, the third vertical constant is equal to zero, the fourth vertical constant is equal to zero, the fifth vertical constant is equal to “1”, and the sixth vertical constant is equal to zero;a second vertical combination in which the first vertical constant is equal to “1”, the second vertical constant is equal to zero, the third vertical constant is equal to zero, the fourth vertical constant is equal to “0.8”, the fifth vertical constant is equal to “1”, and the sixth vertical constant is equal to zero;a third vertical combination in which the first vertical constant is equal to “1”, the second vertical constant is equal to zero, the third vertical constant is equal to zero, the fourth vertical constant is equal to “−0.6”, the fifth vertical constant is equal to “1”, and the sixth vertical constant is equal to zero;a fourth vertical combination in which the first vertical constant is equal to “1”, the second vertical constant is equal to “0.15”, the third vertical constant is equal to zero, the fourth vertical constant is equal to “0.8”, the fifth vertical constant is equal to “1”, and the sixth vertical constant is equal to zero;a fifth vertical combination in which the first vertical constant is equal to “1”, the second vertical constant is equal to “0.15”, the third vertical constant is equal to zero, the fourth vertical constant is equal to “−0.6”, the fifth vertical constant is equal to “1”, and the sixth vertical constant is equal to zero;a sixth vertical combination in which the first vertical constant is equal to “1”, the second vertical constant is equal to “−0.15”, the third vertical constant is equal to zero, the fourth vertical constant is equal to “0.8”, the fifth vertical constant is equal to “1”, and the sixth vertical constant is equal to zero; anda seventh vertical combination in which the first vertical constant is equal to “1”, the second vertical constant is equal to “−0.15”, the third vertical constant is equal to zero, the fourth vertical constant is equal to “−0.6”, the fifth vertical constant is equal to “1”, and the sixth vertical constant is equal to zero. 15. A device for assisted piloting of an aircraft having a rotary wing and a propulsion unit having at least one propulsion propeller, each propeller having a plurality of first blades and the rotary wing having a rotor having a plurality of second blades, the device comprising: control means suitable for being controlled by a pilot to deliver a movement order for movement in a direction;a processor unit connected to the control means, the processor unit executing instructions to transform said order into an acceleration setpoint in said direction, and then to transform said acceleration setpoint, by predetermined relationships, into a required longitudinal attitude setpoint (θ*) and into a first required load factor setpoint (Nx*) in a longitudinal direction of the aircraft parallel to a roll axis of said aircraft;a first automatic system for maintaining longitudinal attitude by controlling a longitudinal cyclic pitch of the second blades of the rotary wing in order to comply with the required longitudinal attitude setpoint (θ*); anda second automatic system for maintaining load factor by controlling a collective pitch of the first blades of the propulsion unit in order to comply with said first load factor setpoint (Nx*). 16. The device according to claim 15, including a third automatic system for maintaining load factor to control the collective pitch of said second blades, said processor unit transmitting a second required load factor setpoint to the third automatic means for maintaining load factor. 17. The device according to claim 16, including a system for determining flight parameters. 18. A hybrid aircraft including a device according to claim 15.