Data processing: measuring – calibrating – or testing – Measurement system – History logging or time stamping
Patent
1997-01-10
2000-02-08
Wachsman, Hal
Data processing: measuring, calibrating, or testing
Measurement system
History logging or time stamping
702144, 702151, 702169, 706905, 706913, 706900, 701 4, 701 14, 701 15, 701 16, 244 1713, G06F 1900
Patent
active
06023668&
DESCRIPTION:
BRIEF SUMMARY
BACKGROUND OF THE INVENTION
The present invention relates to a process for determining the flight configurations of an aircraft, especially a helicopter, as well as to a device for applying said process.
Within the framework of the present invention, flight configuration of an aircraft is understood to mean a flight phase, for example takeoff, landing or level flight, exhibiting determined flight characteristics, and capable of being differentiated from other flight phases, and during which the aircraft is subjected to relatively constant types of stresses.
It is often necessary to know the flight configurations of the aircraft, for example current flight configuration: particular member has been subjected to high stresses requiring its replacement.
Various methods for determining the flight configurations of an aircraft are known.
Firstly, methods are known which apply neural networks which determine the flight configurations from measurements made in-flight and from stored predetermined coefficients. The phase of determining and storing these coefficients is lengthy and cumbersome. Moreover, once set up, these methods can be very difficult to modify, for example in order to be adapted to new knowledge or to technical modifications of the aircraft.
Secondly, a method is known which is based on artificial intelligence and which essentially uses empirical data. This method also requires lengthy application and does not allow all the possible flight configurations to be recognized.
A method may also be cited which is based on analyzing data, in particular specific flight parameters, which method does not however afford completely satisfactory accuracy.
SUMMARY OF THE INVENTION
The object of the present invention is to remedy these drawbacks. It relates to a process making it possible to determine, rapidly and accurately, the flight configurations of an aircraft, in particular a helicopter.
For this purpose, said process is noteworthy according to the invention: defined; are determined; aircraft are determined; said flight phases; and representative of the situation of said flight configuration in a specified metric system is calculated in said metric system, from said measured values of the parameters for the representative flight phases; and parameters are measured; flight configurations, to said flight phase, n being a predefined integer, are determined in said metric system from said measured values; respectively to each of said n closest flight configurations; and the flight configuration of which said flight phase forms part, as appropriate, is deduced from the membership functions thus determined and from the fuzziness indices of these n closest flight configurations.
Thus, by virtue of the invention, the flight configurations of an aircraft can be determined quasi-continuously and accurately, by performing the essentials of the processing operations on a limited number n of predefined flight configurations.
Moreover, as will be seen later, the process according to the invention can be tailored during application, allowing in particular the integration of new undefined flight configurations in said preliminary step.
Advantageously, to calculate the fuzziness index of a flight configuration: configuration are determined in said metric system from the measured values of said parameters; the center of gravity of said flight configuration, is calculated in said metric system from these positions; phase is determined for each of said representative flight phases, in said metric system; each of said flight phases, from the corresponding distance thus determined; and determined.
Furthermore, for a determined flight phase of distance D(Xj,Ci) to the center of gravity of the corresponding flight configuration, the membership function .mu.(Xj) is advantageously defined by the relation: advantageously defined by the relation: ##EQU1## in which: M is a predefined coefficient, configuration, flight configuration, and
Moreover, to determine the n flight configurations closest to a flight phase: relevant flight c
REFERENCES:
patent: 5299759 (1994-04-01), Sherman et al.
patent: 5457634 (1995-10-01), Chakravarty
patent: 5479346 (1995-12-01), Lecomte et al.
Stengel Robert F., "Toward Intelligent Flight Control" IEEE Transactions on Systems, Man, and Cybernetics, vol. 23, No. 6 Nov./Dec. 1993, pp. 1699-1717.
Eurocopter France
Wachsman Hal
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