초록 ▼

An aircraft performance degradation detection system may include information sources, a central unit connected to the information sources, and a warning device that is connected to the central unit. Using information received from the information sources, the central unit computes the current weight

An aircraft performance degradation detection system may include information sources, a central unit connected to the information sources, and a warning device that is connected to the central unit. Using information received from the information sources, the central unit computes the current weight and drag of the aircraft and computes a theoretical drag based on the current weight. The current and theoretical drags are compared, and a determination is made regarding performance degradation based on the comparison.

대표청구항 ▼

I claim: 1. A method for detecting aircraft performance degradation comprising: (a) receiving the initial weight of the aircraft from an external source; (b) computing a current weight of the aircraft based on the received initial weight; (c) computing the drag of the aircraft based on the computed

I claim: 1. A method for detecting aircraft performance degradation comprising: (a) receiving the initial weight of the aircraft from an external source; (b) computing a current weight of the aircraft based on the received initial weight; (c) computing the drag of the aircraft based on the computed current weight; (d) computing a theoretical drag, CXth, of the aircraft based on the value of the computed drag and the square value of the computed drag (e) comparing the computed theoretical drag to a current drag of the aircraft that is computed by a different formula; (f) generating an indication of aircraft performance degradation based on the result of the comparison; and (g) outputting said indication. 2. The method of claim 1, wherein the indication of aircraft performance degradation is an alert message. 3. The method of claim 1, wherein step (b) comprises computing the current weight of the aircraft on the basis of the aircraft's initial weight before the flight and the consumption of fuel during the flight, which depends on the altitude of the aircraft during the flight and on the type of aircraft. 4. The method of claim 1, wherein the current drag, CXa/c, of the aircraft is computed using the expression: in which: R is a constant value, S represents the area of the flying surface of the aircraft, TAS is a computed airspeed, G is a value dependent on TAS, and T is a value of traction. 5. The method of claim 1 further comprising, when a degradation of performance is detected: comparing a measured speed and a computed minimum operational speed relating to severe icing conditions; and emitting a message requesting an increase in speed if the measured speed is less than the computed minimum operational speed. 6. The method of claim 1 performed only when the flaps and landing gear of the aircraft are retracted. 7. The method of claim 1, wherein the comparison of the aircraft's computed theoretical drag and current drag and the indication of aircraft performance degradation is output only if at least one icing condition is fulfilled and if a measured static air temperature is greater than a predetermined value. 8. The method of claim 1, further comprising determining whether the aircraft is in cruising flight, and wherein said indication of aircraft performance degradation is determined, in response to the aircraft being determined not to be in cruising flight, solely on the basis of the comparison result. 9. The method of claim 8, wherein said indication of aircraft performance degradation is determined, in response to the aircraft being determined to be in cruising flight, based on whether one of the following two conditions A and B is fulfilled: condition A: CXa/c>CXth+ΔCX1, for a predetermined duration, and condition B: CXa/c>CXth+ΔCX2 and ΔCXa/c>ΔCXth+ΔCX3 for which: CXa/c is a computed current drag of the aircraft, CXth is the computed theoretical drag of the aircraft, ΔCX1, ΔCX2, and ΔCX3 are predetermined values of drag, ΔCXa/c is a deviation of computed current drag between two different predetermined instants, and ΔCXth is a deviation of computed theoretical drag between two different predetermined instants. 10. The method of claim 1 further comprising: determining whether the aircraft is in cruising flight; and in response to the aircraft being determined to be in cruising flight: computing a theoretical cruising speed based on the computed current weight of the aircraft; measuring a current speed of the aircraft; comparing the measured current speed and the computed theoretical cruising speed; and outputting the indication of aircraft performance degradation based on the comparisons of: (1) the computed theoretical drag to the computed current drag of the aircraft and (2) the measured current speed and the computed theoretical cruising speed. 11. The method of claim 10, wherein the theoretical cruising speed is computed on the basis of the computed current weight of the aircraft, a measured altitude of the aircraft, and the deviation between a standard temperature and a measured temperature. 12. The method of claim 10, wherein aircraft performance degradation is determined to exist if one of the following two conditions C and D is fulfilled: condition C: CXa/c>CXth+ΔCX4 and IASCXth+ΔCX4, IASΔCXth+ΔCX5 for which: CXa/c is a computed current drag of the aircraft, CXth is the computed theoretical drag of the aircraft, ΔCX4 and ΔCX5 are predetermined values of drag, IAS is the measured current speed of the aircraft, IASth is the computed theoretical cruising speed, ΔIAS1 is a predetermined deviation in speed, ΔCXa/c is a deviation in computed current drag between two different predetermined instants, and ΔCXth is a deviation in computed theoretical drag between two different predetermined instants. 13. The method of claim 12, wherein aircraft performance degradation is determined to exist if one of the following two conditions E and F is fulfilled: condition E: CXa/c>CXth+ΔCX6 and IASCXth+ΔCX6, IASΔCXth+ΔCX7 for which: ΔCX6 and ΔCX7 are predetermined values of drag, ΔCX6 is less than ΔCX4, ΔIAS2 is a predetermined deviation of speed, and ΔIAS2 is greater than ΔIAS1. 14. The method as claimed in claim 13, wherein if none of the conditions C, D, E, and F is fulfilled: a check is performed to verify whether one of the following two conditions G and H is fulfilled: condition G: CXa/c>CXth+ΔCX8 and IASCXth+ΔCX8, IASΔCXth+ΔCX9, for which: ΔCX8 and ΔCX9 are predetermined drag values, ΔCX8 being less than ΔCX6, and ΔIAS3 is a predetermined deviation of speed, which is less than ΔIAS1 and ΔIAS2; and if one of the conditions G and H is fulfilled, a message indicating that the cruising speed is low is emitted. 15. A method for detecting aircraft performance degradation comprising: receiving the initial weight of the aircraft from an external source; computing a current weight of the aircraft based on the received initial weight; computing a theoretical drag of the aircraft based on the computed current weight; computing the current drag, CXa/c, of the aircraft using the expression: description="In-line Formulae" end="lead"CXa/c=2.T/R.S.TAS2-G, description="In-line Formulae" end="tail" in which: R is a constant value, S represents the area of the flying surface of the aircraft, TAS is a computed airspeed, G is a value dependent on TAS, and T is a value of traction; comparing the computed theoretical drag to the computed current drag of the aircraft; and outputting an indication of aircraft performance degradation based on the result of the comparison. 16. The method of claim 15, wherein the indication of aircraft performance degradation is an alert message. 17. The method of claim 15, wherein the current weight of the aircraft is computed on the basis of the aircraft's initial weight before the flight and the consumption of fuel during the flight, which depends on the altitude of the aircraft during the flight and on the type of aircraft. 18. The method of claim 15 further comprising, when a degradation of performance is detected: comparing a measured speed and a computed minimum operational speed relating to severe icing conditions; and emitting a message requesting an increase in speed if the measured speed is less than the computed minimum operational speed. 19. The method of claim 15 performed only when the flaps and landing gear of the aircraft are retracted. 20. The method of claim 15, wherein the comparison of the aircraft's computed theoretical drag and current drag and the indication of aircraft performance degradation is output only if at least one icing condition is fulfilled and if a measured static air temperature is greater than a predetermined value. 21. The method of claim 15, further comprising: determining whether the aircraft is in cruising flight; and determining, if the aircraft is determined not to be in cruising flight, whether aircraft performance degradation exists solely on the basis of the comparison result. 22. The method of claim 21, wherein aircraft performance degradation is determined to exist, when the aircraft is determined not to be in cruising flight, if one of the following two conditions A and B is fulfilled: condition A: CXa/c>CXth+ΔCX1, for a predetermined duration; condition B: CXa/c>CXth+ΔCX2 and ΔCXa/c>ΔCXth+ΔCX3 for which: CXa/c is the computed current drag of the aircraft, CXth is the computed theoretical drag of the aircraft, ΔCX1, ΔCX2, and ΔCX3 are predetermined values of drag, ΔCXa/c is a deviation of computed current drag between two different predetermined instants, and ΔCXth is a deviation of computed theoretical drag between two different predetermined instants. 23. The method of claim 15 further comprising: determining whether the aircraft is in cruising flight; and when the aircraft is in cruising flight: computing a theoretical cruising speed based on the computed current weight of the aircraft; measuring a current speed of the aircraft; comparing the measured current speed and the computed theoretical cruising speed; and outputting the indication of aircraft performance degradation based on the comparisons of: (1) the computed theoretical drag to the computed current drag of the aircraft and (2) the measured current speed and the computed theoretical cruising speed. 24. The method of claim 23, wherein the theoretical cruising speed is computed on the basis of the computed current weight of the aircraft, a measured altitude of the aircraft, and the deviation between a standard temperature and a measured temperature. 25. The method of claim 23, wherein aircraft performance degradation is determined to exist if one of the following two conditions C and D is fulfilled: condition C: CXa/c>CXth+ΔCX4 and IASCXth+ΔCX4, IASΔCXth+ΔCX5 for which: CXa/c is the computed current drag of the aircraft, CXth is the computed theoretical drag of the aircraft, ΔCX4 and ΔCX5 are predetermined values of drag, IAS is the measured current speed of the aircraft, IASth is the computed theoretical cruising speed, ΔIAS1 is a predetermined deviation in speed, ΔCXa/c is a deviation in computed current drag between two different predetermined instants, and ΔCXth is a deviation in computed theoretical drag between two different predetermined instants. 26. The method of claim 25, wherein aircraft performance degradation is determined to exist if one of the following two conditions E and F is fulfilled: condition E: CXa/c>CXth+ΔCX6 and IASCXth+ΔCX6, IASΔCXth+ΔCX7 for which: ΔCX6 and ΔCX7 are predetermined values of drag, ΔCX6 is less than ΔCX4, ΔIAS2 is a predetermined deviation of speed, and ΔIAS2 is greater than ΔIAS1. 27. The method as claimed in claim 26, wherein if none of the conditions C, D, E, and F is fulfilled: a check is performed to verify whether one of the following two conditions G and H is fulfilled: condition G: CXa/c>CXth+ΔCX8 and IASCXth+ΔCX8, IASΔCXth+ΔCX9, for which: ΔCX8 and ΔCX9 are predetermined drag values, ΔCX8 being less than ΔCX6, and ΔIAS3 is a predetermined deviation of speed, which is less than ΔIAS1 and ΔIAS2; and if one of the conditions G and H is fulfilled, a message indicating that the cruising speed is low is emitted. 28. A device for detecting aircraft performance degradation comprising: a set of information sources; a first computer that computes a current weight of the aircraft based on the initial weight of the aircraft obtained from the set of information sources; a second computer that computes a value of aircraft drag based on the computed current weight and computes a theoretical drag, CXth, of the aircraft based on the computed value of drag and the square of the computed value of drag; a first comparator that compares the computed theoretical drag to a current drag of the aircraft that is computed by a different formula; and a warning indicator that indicates aircraft performance degradation based on the result of the comparison. 29. The device of claim 28 further comprising: a third computer that computes a theoretical cruising speed based on the computed current weight of the aircraft; a measuring section that measures a current speed of the aircraft; and a second comparator that compares the measured current speed and the computed theoretical cruising speed, wherein the warning indicator indicates aircraft performance degradation based on the comparisons of: (1) the computed theoretical drag to the computed current drag of the aircraft and (2) the measured current speed and the computed theoretical cruising speed. 30. The device of claim 28, wherein the set of information sources comprises a flight data acquisition unit. 31. The device of claim 28, wherein the warning indicator comprises an aircraft performance interface unit.