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The detection device includes, but is not limited to a device that is configured to determine a control error corresponding to the difference between a first control instruction and a control surface position, a second device that is configured to calculate the difference between this control error

The detection device includes, but is not limited to a device that is configured to determine a control error corresponding to the difference between a first control instruction and a control surface position, a second device that is configured to calculate the difference between this control error and a second control instruction in such a way as to form a comparison signal, and a third device that is configured to detect a jamming of the control surface if this comparison signal is greater than a threshold value.

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1. A method for detecting a jamming of a control surface, a position of the control surface is controlled by a feedback loop that forms a part of an electrical flight control system of an aircraft, the feedback loop comprising: a plurality of actuators coupled to the control surface to adjust the po

1. A method for detecting a jamming of a control surface, a position of the control surface is controlled by a feedback loop that forms a part of an electrical flight control system of an aircraft, the feedback loop comprising: a plurality of actuators coupled to the control surface to adjust the position of the control surface in relation to the aircraft according to at least one actuation instruction received as a control command;at least one sensor configured to measure an actual position of said control surface; andat least one computer that is configured to produce a control surface control instruction, which receives said actual position and produces an actuation instruction that is transmitted to one of said plurality of actuators in a form of a control current,wherein the method comprises:receiving as input a first control instruction of the control surface from a device onboard the aircraft, the first control instruction limited to maximum operational values;filtering the first control instruction signal using a filter that models a behavior of the one of said plurality of actuators and the feedback loop;determining a control error corresponding to a difference between the filtered first control instruction of the control surface and a corresponding control surface position;forming a comparison signal with a difference between an absolute value of said control error and the absolute value of a second control instruction of the control surface, the second control instruction shielded from said control error;comparing the comparison signal with a threshold value; anddetecting a jamming of said control surface if the comparison signal is greater than the threshold value during at least a confirmation period;reconfiguring a second one of the plurality of actuators to adjust the position of the control surface based on the detection of the jamming of the control surface. 2. The method as claimed in claim 1, wherein said control error E is calculated using the following expression: E=|isv/K|where:isv represents the control current applied to the at least one actuator; andK represents a control gain. 3. The method as claimed in claim 1, wherein a measured position is used for said position of the control surface. 4. The method as claimed in claim 1, further comprising using a calculated position for said position of the control surface. 5. The method as claimed in claim 1, further comprising limiting said position of the control surface. 6. The method as claimed in claim 1, further comprising limiting and said second control instruction. 7. The method as claimed in claim 1, wherein the threshold value is a variable according to particular conditions. 8. The method as claimed in claim 1, further comprising starting after satisfying particular activation conditions. 9. The method as claimed in claim 1, wherein the filter is a second-order discrete linear filter, and adjustment parameters are optimized to improve a response and stability of said filter. 10. The method as claimed in claim 1, wherein , switching the at least one actuator to a passive mode, and switching an auxiliary actuator previously in the passive mode to an active mode with a function to adjust the position of said control surface if the jamming is detected. 11. The method as claimed in claim 1, wherein for the control surface to be controlled by a plurality of actuators, confirming a jamming of the control surface if a jamming is detected for a predetermined number of said plurality of actuators. 12. The method as claimed in claim 1, further comprising transmitting an alarm if the jamming is detected. 13. A device for detecting a jamming of a control surface of an aircraft, a feedback loop forming a part of an electrical flight control system of the aircraft, comprising: a plurality of actuators coupled to the control surface to adjust a position of the control surface in relation to the aircraft and one of the plurality of actuators configured to adjust the position of the control surface according to at least one actuation instruction received from a device onboard the aircraft as a control command;at least one sensor configured to measure an actual position of said control surface; anda computer that is configured to produce a control surface control instruction, which receives said actual position and which deduces an actuation instruction that is transmitted to the one of the plurality of actuators as a control current;a filter that filters a first control instruction for the control surface based on a behavior of the one of the plurality of actuators and the feedback loop;a first device that determines a control error corresponding to a difference between the filtered first control instruction of the control surface and a corresponding control surface position;a second device that calculates a difference between an absolute value of said control error and the absolute value of a second control instruction of the control surface in such a way as to form a comparison signal, the second control instruction shielded from said control error;a third device that compares the comparison signal with a threshold value;a fourth device that detects a jamming of said control surface if the comparison signal is greater than the threshold value during at least a confirmation period; anda fifth device that reconfigures a second one of the plurality of actuators to adjust the position of the control surface based on the detection of the jamming of the control surface. 14. The device as claimed in claim 13, wherein said control error E is calculated using the following expression: E=|isv/K|where:isv represents the control current applied to the at least one actuator; andK represents a control gain. 15. The device as claimed in claim 13, wherein the threshold value is a variable according to particular conditions. 16. The device as claimed in claim 13, further comprising an alarm that is configured to activate if the jamming is detected. 17. An electrical flight control system of an aircraft, comprising: at least device that is configured to produce a control surface control instruction for a mobile control surface of the aircraft and at least one feedback control loop to control a position of this control surface, comprising:a plurality of actuators coupled to the mobile control surface and one of the plurality of actuators adjusts the position of said mobile control surface in relation to the aircraft according to at least one actuation instruction received from a device onboard the aircraft;at least one sensor that is configured to measure an actual position of said control surface; anda computer that is configured to produce said control surface control instruction, which receives said actual position and which deduces an actuation instruction that is transmitted to the one of the plurality of actuators; anda detection device, the detection device comprising;a filter that filters a first control instruction for the mobile control surface based on a behavior of the one of the plurality of actuators and the at least one feedback control loop;a first device that determines a control error corresponding to a difference between the filtered first control instruction of the control surface and a corresponding control surface position;a second device that calculates a difference between an absolute value of said control error and the absolute value of a second control instruction of the control surface in such a way as to form a comparison signal, the second control instruction shielded from the control error;a third device that compares the comparison signal with a threshold value;a fourth device that detects a jamming of said control surface if the comparison signal is greater than the threshold value during at least a confirmation period; anda fifth device that reconfigures a second one of the plurality of actuators to adjust the position of the control surface based on the detection of the jamming of the control surface. 18. The electrical flight control system as claimed in claim 17, wherein said control error E is calculated using the following expression: E=|isv/K|where:isv represents a control current applied to the at least one actuator; andK represents a control gain.