초록 ▼

A method for testing a component part of an aircraft comprises the steps of determining at least one first test value of the component part of the aircraft and/or at least one first test value of a comparable component part of a further aircraft for at least one test parameter, inputting the first t

A method for testing a component part of an aircraft comprises the steps of determining at least one first test value of the component part of the aircraft and/or at least one first test value of a comparable component part of a further aircraft for at least one test parameter, inputting the first test parameter and the first test value into a pattern recognition system, which produces an inner correlation between the first test parameter and the first test value. The method further comprises the steps of defining at least one second test parameter, inputting the second test parameter into the pattern recognition system in order to determine a second test value by means of the inner correlation, checking whether the second test value falls within the predefined value range, and determining a third test value of the component part of the aircraft for the second test parameter if the second test value falls within the predefined value range. The invention further relates to a device for testing a component part of an aircraft.

대표청구항 ▼

1. A method for producing inner correlations between test parameters and test values and for selecting test parameters for testing a component part of an aircraft, said method comprising the steps of: a) measuring, using at least one measurement arrangement, a first test value for a first test param

1. A method for producing inner correlations between test parameters and test values and for selecting test parameters for testing a component part of an aircraft, said method comprising the steps of: a) measuring, using at least one measurement arrangement, a first test value for a first test parameter of the component part of the aircraft, said first test parameter representing a specification for changing or manipulating the component part and said measuring first test value is performed during a change or manipulation of said component part corresponding to the first test parameter;b) automatically inputting said first test parameter and said first test value into a pattern recognition system, and producing an inner correlation between said first test parameter and said first test value, said inner correlation representing a relationship between said first test parameter and said first test value;c) defining at least one second test parameter of the component part of the aircraft using a test parameter definition procedure;d) automatically inputting said second test parameter into said pattern recognition system in order to determine a second test value, wherein the second test value is a predicted value based on the inner correlation;e) checking whether the second test value falls within a predefined value range; andf) measuring, using the at least one measurement arrangement, a third test value of said component part of the aircraft for the second test parameter when the second test value falls within the predefined value range. 2. The method as claimed in claim 1, wherein the first test value and/or the third test value is/are measured by a mechanical and/or electrical measurement, and in order to determine the third test value, the first test parameter further being replaced by the second test parameter if the second test value falls within the predefined value range, the second test value being determined from the second test parameter which replaces the first test parameter, or from the first test parameter and the second test parameter which replaces the first test parameter. 3. The method as claimed in claim 1, wherein the first test parameter and/or the second test parameter comprise/comprises at least one component from the following group: extent of manipulation of the component part, location of manipulation of the component part, method of manipulation of the component part or duration of manipulation of the component part. 4. The method as claimed in claim 1, wherein the pattern recognition system is formed as a neural network. 5. The method as claimed in claim 1, wherein, in step c), the test parameter definition procedure defines the second test parameter randomly or in a manner based on a stochastic distribution. 6. The method as claimed in claim 1, wherein the test parameter definition procedure includes before step c), forming the center point of a cluster of first test parameters or of first test values, the center point being used as a starting point for the definition of the second test parameter, orusing the first test values which fall within the predefined value range as starting points for the definition of the second test parameter. 7. The method as claimed in claim 1, wherein step c) is provided by a genetic algorithm, the second test parameter being generated from the combination of two or more first test parameters, the type and manner of the combination further being performed randomly. 8. The method as claimed in claim 1, wherein the predefined value range is a range of a probability distribution which specifies the probability for a fault of the component part according to the second test parameter, the probability for a fault for the predefined value range being greater than 80%, or being less than 20%. 9. The method as claimed in claim 1, wherein the component part is a control arrangement, in particular a control arrangement for an ambient control system of a cabin of the aircraft or a control arrangement for steering the aircraft, the first test parameter and/or the second test parameter comprising: external temperature, internal temperature in the cabin, altitude of the aircraft, aircraft weight and/or center of gravity of the aircraft. 10. The method as claimed in claim 1, wherein the component part is a power supply arrangement, which provides power at various supply points in the cabin and/or at a kitchen of the aircraft, the first test parameter and/or the second test parameter comprising: the moment of connection of the power consumption at a supply point, the moment of disconnection of the power consumption at a supply point, the power consumption at a supply point, the number of interruptions of the power supply between two supply points, and/or the duration of the interruptions of the power supply between two supply points. 11. The method as claimed in claim 1, wherein the component part is an electrically operated valve, the first test parameter and/or the second test parameter comprising the moment of interruption of the power supply of the valve, the number of power interruptions, the duration of the power interruptions, and/or the interval between two power interruptions. 12. The method according to claim 1, further comprises automatically inputting the determined second test parameter and the third test value into the pattern recognition system to replace the first test parameter and the first test value respectively and produce another inner correlation between the first test parameter and first test value. 13. The method according to claim 1, wherein the steps a) to f) are performed in a specified order. 14. The method according to claim 1, wherein the steps a) to f) are carried out repeatedly to train the produced inner correlation and select further second test parameters. 15. The method according to claim 1, wherein the steps a) to b) are carried out repeatedly to train the produced inner correlation and select further second test parameters. 16. A device for producing inner correlations between test parameters and test values and for selecting test parameters for testing a component part of an aircraft, comprising a measuring arrangement, which is suitable for measuring a first test value for a first parameter, the first test parameter representing a specification for changing or manipulating the component part and the measuring arrangement measuring the first test value during a change or manipulation of the component part corresponding to the first test parameter,a pattern recognition system, which is suitable for producing an inner correlation between the first test value and the first test parameter, the inner correlation representing a relationship between the first test parameter and the first test value, and for generating a second test value from a second test parameter by predicting the second test value based on the inner correlation,a test parameter definition arrangement, which defines the second test parameter of the component part of the aircraft,a selection arrangement, which is suitable for dividing a second test value into classes,the measuring arrangement measuring a third test value on the basis of the second test parameter if the second test value falls within a predefined one of the classes. 17. The device as claimed in claim 16, wherein the measuring arrangement determines the first test value and/or the third test value by a mechanical and/or electrical measurement. 18. The device as claimed in claim 16, wherein a plurality of first test parameters are provided, the test parameter definition arrangement defining a plurality of second test parameters, andthe selection arrangement further replacing at least one first test parameter by at least one second test parameter if the second test value falls within the predefined class, the pattern recognition system determining the second test value from the second test parameter which replaces the first test parameter, orthe pattern recognition system determining the second test value from at least one first test parameter and the at least one second test parameter which replaces the first test parameter. 19. A method for producing correlations between test parameters and test values comprising: measuring a first test value of the component part of an aircraft wherein the first test value corresponds to a first test parameter representing a specification for changing or manipulating the component part, wherein the first test value is measured during a change or manipulation of the component part corresponding to the first test parameter;automatically inputting the first test parameter and the first test value into a pattern recognition system, and producing an inner correlation between the first test parameter and the first test value;defining a second test parameter of the component part of the aircraft using a test parameter definition procedure;automatically inputting the second test parameter into the pattern recognition system to produce a second test value, wherein the second test value is a predicted value based on the inner correlation;determining whether the second test value falls within a predefined value range; andin response to the determination that the second test value falls within the predefined value range, measuring a third test value of the component part of the aircraft, wherein the third test value corresponds to the second test parameter. 20. The method of claim 19, further comprises automatically inputting the determined second test parameter and the measured third test value into the pattern recognition system to replace the first test parameter and the first test value respectively and produce another inner correlation between the first test parameter and first test value.