초록 ▼

An electric control system (1) comprises a control unit (4) which comprises a member (5) able to be actuated by a pilot and a means of load-wise protection (7), and which delivers a first deflection order representative of the action exerted by the pilot on the member (5), and of the contribution ma

An electric control system (1) comprises a control unit (4) which comprises a member (5) able to be actuated by a pilot and a means of load-wise protection (7), and which delivers a first deflection order representative of the action exerted by the pilot on the member (5), and of the contribution made by the means of load-wise protection (7), an actuator (11) which moves said control surface (2) about an axis (Z?Z), as a function of a deflection order, and a correction device (12) which comprises a means (13) for determining a second deflection order making it possible to limit the load, to which a stabilizer element of the aircraft is subjected, to a maximum load, and a means (14) for choosing one of the first and second deflection orders, which is transmitted to said actuator (11) so as to move said control surface (2).

대표청구항 ▼

1. A process for moving a control surface of an aircraft in such a way as to reduce the induced loads to which a stabilizer element of said aircraft is subjected, said control surface being mounted rotatably about an axis so as to be able to take any angular position of deflection within a range of

1. A process for moving a control surface of an aircraft in such a way as to reduce the induced loads to which a stabilizer element of said aircraft is subjected, said control surface being mounted rotatably about an axis so as to be able to take any angular position of deflection within a range of travel and being moved in accordance with a deflection order applied thereto, and maid aircraft comprising a control unit able to determine a first deflection order as a function of at least the actuation of a control member by a pilot of the aircraft, wherein the following series of successive operations is carried out automatically and repetitively:a) a first value is determined, dependent on the maximum load to which said stabilizer element may be subjected; b) a second value is determined, taking into account the actual load to which said stabilizer element is subjected, when said first deflection order determined by said control unit is applied to said control surface; c) said first and second values are intercompared; and d) as a function of this comparison: if said second value is less than or equal to said first value, said first deflection order is applied to said control surface; and if said second value is greater than said first value, a second deflection order is calculated, making it possible to limit the load to which said stabilizer element is subjected to said maximum load, and this second deflection order is applied to said control surface, wherein: said first value corresponds to said maximum load which is predetermined, said second value corresponds to said actual load, and said actual load Mx is determined from the following expression: in which:ρ is the density of the airs S is the surface area of the stabilizer element; V is the air speed; Z1 is the lever arm between the center of application of the aerodynamic load due to sideslip and the axis of calculation of the moment; C1 is a lateral force coefficient, relating to the stabilizer element for the sideslip effect; βr is the sideslip; Z2 is the lever arm between the center of application of the aerodynamic load due to the deflection of the control surface and the axis of calculation of the moment; C2 is a lateral force coefficient, relating to the stabilizer element, as a function of the deflection of the control surface; and δrmes is a measured deflection angle. 2. The process as claimed in claim 1, wherein said second deflection order δrmax is determined from the following expression: in which:Mxmax is said maximum load; ρ is the density of the air; S is the surface area of the stabilizer element; V is the air speed; Z1 is the lever arm between the center of application of the aerodynamic load due to sideslip and the axis of calculation of the moment; C1 is a lateral force coefficient, relating to the stabilizer element for the sideslip effect; βr is the sideslip; Z2 is the lever arm between the center of application of the aerodynamic load due to the deflection of the control surface and the axis of calculation of the moment; and C2 is a lateral force coefficient, relating to the stabilizer element, as a function of the deflection of the control surface. 3. The process as claimed in claim 1, wherein said maximum load is less than a predetermined percentage of a limit load relating to said stabilizer element.4. The process as claimed in claim 1, wherein the application of said second deflection order is disabled during at least one particular flight configuration of the aircraft.5. A process for moving a control surface of an aircraft in such a way as to reduce the induced loads to which a stabilizer element of said aircraft is subjected, said control surface being mounted rotatably about an axis so as to be able to take any angular position of deflection within a range of travel and being moved in accordance with a deflection order applied thereto, and said aircraft comprising a control unit able to determine a first deflection order as a function of at least the actuation of a control member by a pilot of the aircraft, wherein the following series of successive operations is carried out automatically and repetitively:a) a first value is determined, dependent on the maximum load to which said stabilizer element may be subjected; b) a second value is determined, taking into account the actual load to which said stabilizer element is subjected, when said first deflection order determined by said control unit is applied to said control surface; c) said first and second values are intercompared; and d) as a function of this comparison: if said second value is less than or equal to said first value, said first deflection order is applied to said control surface, and if said second value is greater than said first value, a second deflection order is calculated, making it possible to limit the load to which said stabilizer element is subjected to said maximum load, and this second deflection order is applied to said control surface, wherein: said first value corresponds to said second deflection order, said second value corresponds to said first deflection order, and said second deflection order δrmax is determined from the following expression: in which:Mxmax is said maximum load; ρ is the density of the air; S is the surface area of the stabilizer element; V is the air speed; Z1 is the lever arm between the center of application of the aerodynamic load due to sideslip and the axis of calculation of the moment; C1 is a lateral force coefficient, relating to the stabilizer element for the sideslip effect; βr is the sideslip; Z2 is the lever arm between the center of application of the aerodynamic load due to the deflection of the control surface and the axis of calculation of the moment; and C2 is a lateral force coefficient, relating to the stabilizer element, as a function of the deflection of the control surface. 6. The process as claimed in claim 1, wherein said maximum load is less than a predetermined percentage of a limit load relating to said stabilizer element.7. The process as claimed in claim 1, wherein the application of said second deflection order is disabled during at least one particular flight configuration of the aircraft.8. An electric control system for moving a control surface of an aircraft, said control surface being mounted rotatably about an axis so as to be able to take any angular position of deflection within a range of travel, and said system comprising:a control unit which comprises at least one control member able to be actuated by a pilot and at least one means of load-wise protection, and which delivers a first deflection order representative, on the one hand, of the action exerted by the pilot on said control member, and, on the other hand, of the contribution made by said means of load-wise protection; and an actuator which moves said control surface about said axis, as a function of a deflection order received, which system moreover includes a correction device which comprises: a first means for determining a second deflection order making it possible to limit the load, to which maid stabilizer element is subjected, to a maximum load; and a second means for choosing one of said first and second deflection orders, which is transmitted to said actuator so as to move said control surface, said second means intercomparing: a first value dependent on the maximum load, to which said stabilizer element may be subjected; and a second value taking account of the actual load, to which said stabilizer element is subjected when maid first deflection order determined by said control unit is applied to said actuator, and said second means transmitting to said actuator, as a function of this comparison: if said second value is less than or equal to said first value, said first deflection order; and if said second value is greater than said first value, said second deflection order making it possible to limit the load, to which said stabilizer element is subjected, to said maximum load, wherein: said first value corresponds to said maximum load which is predetermined, said second value corresponds to said actual load, and said actual load Mx is determined from the following expression: in which:ρ is the density of the air; S is the surface area of the stabilizer element; V is the air speed; Z1 is the lever arm between the center of application of the aerodynamic load due to sideslip and the axis of calculation of the moment; C1 is a lateral force coefficient, relating to the stabilizer element for the sideslip effect; βr is the sideslip; Z2 is the lever arm between the center of application of the aerodynamic load due to the deflection of the control surface and the axis of calculation of the moment; C2 is a lateral force coefficient, relating to the stabilizer element, as a function of the deflection of the control surface; and δrmes is a measured deflection angle. 9. The system as claimed in claim 8, wherein said second means is a voter.10. The system as claimed in claim 8, which system moreover comprises a third means for disabling said correction device.11. An electric control system for moving a control surface of an aircraft, said control surface being mounted rotatably about an axis so as to be able to take any angular position of deflection within a range of travel, and said system comprising:a control unit which comprises at least one control member able to be actuated by a pilot and at least one means of load-wise protection, and which delivers a first deflection order representative, on the one hand, of the action exerted by the pilot on said control member, and, on the other hand, of the contribution made by said means of load-wise protection; and an actuator which moves maid control surface about said axis, as a function of a deflection order received, which system moreover includes a correction device which comprises: a first means for determining a second deflection order making it possible to limit the load, to which said stabilizer element is subjected, to a maximum load; and a second means for choosing one of said first and second deflection orders, which is transmitted to said actuator so as to move said control surface, said second means intercomparing: a first value dependent on the maximum load, to which said stabilizer element may be subjected; and a second value taking account of the actual load, to which said stabilizer element is subjected when said first deflection order determined by said control unit is applied to said actuator, and said second means transmitting to said actuator, as a function of this comparison: if said second value is less than or equal to said first value, said first deflection order; and if said second value is greater than said first value, said second deflection order making it possible to limit the load, to which said stabilizer element is subjected, to said maximum load, wherein: said first value corresponds to said second deflection order, said second value corresponds to said first deflection order, and said second deflection order δrmax is determined from the following expression: in which:Mxmax is said maximum load; ρ is the density of the air; S is the surface area of the stabilizer element; V is the air speed; Z1 is the lever as between the center of application of the aerodynamic load due to sideslip and the axis of calculation of the moment; C1 is a lateral force coefficient, relating to the stabilizer element for the sideslip effect; βr is the sideslip; Z2 is the lever arm between the center of application of the aerodynamic load due to the deflection of the control surface and the axis of calculation of the moment; and C2 is a lateral force coefficient, relating to the stabilizer element, as a function of the deflection of the control surface. 12. The system as claimed in claim 11, wherein said second means is a voter.13. The system as claimed in claim 11, which system moreover comprises a third means for disabling said correction device.