초록 ▼

A detection device determines whether an uncontrolled movement of a control surface of an aircraft is occurring. The device includes means for calculating the difference between a theoretical command and an actual command in order to form a residual value, and means for detecting an uncontrolled mov

A detection device determines whether an uncontrolled movement of a control surface of an aircraft is occurring. The device includes means for calculating the difference between a theoretical command and an actual command in order to form a residual value, and means for detecting an uncontrolled movement of the control surface, if a comparison value depending on this residual value is greater than a threshold value If the comparison value is greater than the threshold value during a confirmation time, then the uncontrolled movement of the control surface of the aircraft is confirmed.

대표청구항 ▼

1. A detection method for an uncontrolled movement of a control surface which is servo-controlled in position by a feedback loop belonging to an electrical flying command system of the aircraft and comprising: the control surface being mobile and the position of which with respect to the aircraft is

1. A detection method for an uncontrolled movement of a control surface which is servo-controlled in position by a feedback loop belonging to an electrical flying command system of the aircraft and comprising: the control surface being mobile and the position of which with respect to the aircraft is adjusted by at least one actuator;the actuator that adjusts the position of the control surface as a function of at least one actuating order received as a feedback command;at least one sensor measuring the effective position of the control surface; andat least one calculator developing a control surface command order, that receives the measured effective position and deducts from it an actuating order that is transmitted to the actuator as a feedback command,a method where on an automatic and repetitive way, the following sequence of successive steps is followed:(a) a theoretical feedback current being representative of the feedback command emitted bay the calculator is determined;(b) a parameter being representative of the feedback command is measured with the help of at least one auxiliary sensor at the level of the mechanization of such command into the actuator and an effective feedback current is determined from the measured parameter;(c) the difference between the theoretical feedback current determined at step (a) and the effective feedback current determined at step (b) is calculated so as to form an error signal; and(d) an uncontrolled movement of the control surface is detected if a comparison value depending on the error signal is higher than a threshold value during at least one confirmation time. 2. The method according to claim 1, wherein at step (a), the theoretical feedback current corresponds to the current emitted by the calculator. 3. The method according to claim 1, wherein at step (a), the theoretical feedback current is calculated thru auxiliary calculation means on the same way as the calculator calculates the emitted current. 4. The method according to claim 3, wherein at step (a), the calculated theoretical feedback current is limited. 5. The method according to claim 1, wherein at least one of the following values: threshold value and confirmation time, is variable as a function of particular conditions. 6. The method according to claim 1, wherein it is checked if particular activation conditions are fulfilled, and in that the set of the steps (a) to (d) is implemented when these particular activation conditions are fulfilled. 7. The method according to claim 1, wherein the comparison value corresponds to the error signal. 8. The method according to claim 1, wherein an intermediate step is implemented between the steps (c) and (d), upon which the error signal is filtered to obtain said comparison value. 9. The method according to claim 8, wherein at the intermediate step, a Kalman filter is used, control parameters of which are optimized to improve the response and the stability of the filter. 10. The method according to claim 1, wherein, in the case of a detection of an uncontrolled movement at step (a), the actuator is automatically switched into a passive mode and an auxiliary actuator which was previously in a passive mode is automatically switched into an active mode, in which it has then as a function to adjust the position of the control surface. 11. The method according to claim 1, wherein, in the case of a detection of an uncontrolled movement at step (d), a detection piece of information is emitted. 12. A detection device for an uncontrolled movement of a control surface of an aircraft which is servo-controlled in position by a feedback loop, said feedback loop belonging to an electrical flying command system the aircraft and comprising: said control surface being mobile and the position of which with respect to the aircraft is adjusted by at least one actuator;said actuator that adjusts the position of the control surface as a function of at least one actuating order received as a feedback command;at least one sensor measuring the effective position of said control surface; andone calculator developing a control surface command order, that receives said measured effective position and deducts from it an actuating order that is transmitted to said actuator as a feedback command,said device comprising:first means to determine a theoretical feedback current representative of said feedback command emitted by said calculator;at least one auxiliary sensor being connected to said actuator and which is provided so as to measure a parameter representative of the feedback command from which an effective feedback current is determined;second means to calculate the difference between said theoretical feedback current and said effective feedback current so as to create an error signal; andthird means detect an uncontrolled movement of the control surface if a comparison value depending on said error signal is higher than a threshold value during at least one confirmation time. 13. The device according to claim 12, wherein said actuator adjusting the position of said control surface is a hydraulic actuator, and in that said auxiliary sensor is arranged at the level of a slide of a servo valve. 14. The device according to claim 12, wherein said actuator that adjusts the position of said control surface is a hydraulic actuator, and in that said auxiliary sensor is arranged at the level of an electrical engine of the latter. 15. An electrical flying command system of an aircraft, said system comprising: at least one means generate a command order for a control surface for at least one control surface the aircraft; andat least one feedback loop in position of such control surface , comprising:said control surface being mobile and the position of which with respect to the aircraft is adjusted by at least one actuator;said actuator that adjusts the position of the control surface as a function of at least one actuating order received;at least one sensor measuring the effective position of said control surface ; andone calculator developing a control surface command order, that receives said measured effective position and deducts from it an actuating order that is transmitted to said actuator,a detection device , which comprises:first means to determine a theoretical feedback current representative of said feedback command emitted by said calculator;at least one auxiliary sensor being connected to said actuator and which is provided so as to measure a parameter representative of the feedback command from which an effective feedback current is determined;second means to calculate the difference between said theoretical feedback current and said effective feedback current so as to create an error signal; andthird means to detect an uncontrolled movement of the control surface if a comparison value depending on said error signal is higher than a threshold value during at least one confirmation time.