Process and device for determining the flight configurations of an aircraft

• US 6,023,668 A
• Filed: 01/10/1997
• Issued: 02/08/2000
• Est. Priority Date: 05/17/1995
• Status: Expired due to Fees

• Current Assignee: Eurocopter France
• Original Assignee: Eurocopter France
• Inventors: Genoux, Gerard Charles Louis
• Primary Examiner(s): WACHSMAN, HAL D
• Application Number:
  US08/765,794
• Time in Patent Office: 1,124 Days
• Field of Search: 702/187, 702/33, 702/41-44, 702/56, 702/92-97, 702/103, 702/105, 702/113-115, 702/138, 702/140, 702/141, 702/144, 702/145, 702/147, 702/148, 702/130, 702/99 , 702/150-153, 702/169, 702/175, 702/179, 702/FOR 123, 702/182-185, 702/FOR 124, 702/FOR 126, 702/FOR 134, 702/FOR 135 , 702/FOR 139, 702/FOR 142, 702/FOR 144, 702/FOR 145, 702/FOR 150, 702/FOR 151, 702/FOR 152, 364/528.1, 364/528.15, 364/528.34, 364/528.4, 364/528.36-528.39, 706/1, 706/2, 706/4, 706/7, 706/8, 706/900, 706/905, 706/913, 244/17.13, 244/75 R, 244/76 R, 244/175, 244/177-188, 244/194, 244/195, 244/203, 244/227, 244/228, 701/3-5, 701/7, 701/8, 701/10, 701/11, 701/14-16, 73/178 H, 345/500.29
• US Class Current: 702/187
• CPC Class Codes: G05D 1/101 specially adapted for aircraft
• CPC Class Codes: Y10S 706/90 Fuzzy logic
• CPC Class Codes: Y10S 706/905 Vehicle or aerospace
• CPC Class Codes: Y10S 706/913 Vehicle or aerospace

Abstract

A process and system for determining the flight configurations of an aircraft are disclosed. The process includes the steps of defining various possible flight configurations of the aircraft, determining a plurality of flight phases representative of the flight configurations, determining a plurality of characteristic parameters capable of being measured on the aircraft, measuring values of the characteristic parameters for each of the flight phases of the aircraft, calculating a fuzziness index for each of the flight configurations from the measured values of the characteristic parameters for the flight phases, the fuzziness index being representative of the flight configuration in a specified metric system, and defining an actual flight phase of the aircraft.

Claims

1. A process for determining the flight configurations of an aircraft, comprising the steps of:

defining a plurality of flight configurations of the aircraft;

determining a plurality of flight phases representative of each of said flight configurations;

determining a plurality of characteristic parameters capable of being measured on the aircraft;

measuring values of said characteristic parameters for each of said flight phases of the aircraft;

calculating a fuzziness index for each of said flight configurations from said measured values of said characteristic parameters for said flight phases, each of said fuzziness indices being representative of one of said flight configurations in a metric system; and

defining an actual flight phase of said aircraft including the steps of;

measuring values of said characteristic parameters during said actual flight phase;

determining in said metric system a predefined integer number n of flight configurations from among said defined flight configurations which are closest to said actual flight phase based on said measured values;

determining a membership function for said actual flight phase in relation to each of said n closest flight configurations; and

deducing a flight configuration corresponding to said actual flight phase from said membership functions and from said fuzziness indices of said n closest flight configurations.

2. The process as claimed in claim 1, wherein said calculating step comprises the steps of:

determining a plurality of positions of flight phases representative of said n flight configurations in said metric system from said measured values of said characteristic parameters;

determining in said metric system a center of gravity for each of said determined positions that corresponds to the center of gravity of said n flight configurations;

determining in said metric system, for each of said representative flight phases, a distance between each of said centers of gravity and a position of each said representative flight phase;

determining said membership function in said n flight configurations for each of said representative flight phases from said determined distance; and

calculating said fuzziness index from said membership function.

3. The process as claimed in claim 2, wherein said distances are calculated from the relation:

##EQU6## in which;

Xj is the position of a flight phase in said metric system,

R is the position of the center of gravity of a flight configuration in said metric system,

t is a predefined coefficient, and

σ

represents the diagonal matrix of variances of said flight configuration.

4. The process as claimed in claim 1, wherein Xj is the position of a flight phase in said metric system, wherein Ci is one of said flight configurations, and wherein for a determined flight phase of distance D (Xj, Ci) to the center of gravity of the corresponding flight configuration, the membership function μ

(Xj) is defined by the relation;

space="preserve" listing-type="equation">μ

(iXj)=exp(-D(Xj, Ci)).

5. The process as claimed in claim 4, wherein a fuzziness index ν

(Ci) of a flight configuration is defined by the relation;

##EQU7## in which;

Xj is the position of a flight phase in said metric system,

M is a predefined coefficient,

L is the number of flight phases representative of said flight configuration,

μ

(Xj) represents the membership function of a flight phase in said flight configuration, and

S(x) is Shannon'"'"'s entropy function, defined by;

space="preserve" listing-type="equation">S(x)=-x.Log(x)-(1-x).Log(1-x).

6. The process as claimed in claim 1, wherein the step of determining the n flight configurations closest to a flight phase comprises the steps of.

for each one of said defined flight configurations, calculating in said metric system a distance between a flight phase and the center of gravity of said one flight configuration;

comparing said distances thus calculated; and

picking the n flight configurations with the smallest distances.

7. The process as claimed in claim 6, wherein said distances are calculated from the statistical distance of Mahalanobis in the corresponding metric system.

8. The process as claimed in claim 1 wherein said deducing step comprises the step of determining which of the n closest flight configurations satisfy a condition in which the membership function of the flight phase is greater than or equal to the product K.ν

(Ci), in which K represents a coefficient less than or equal to 1 and ν

(Ci) is the calculated fuzziness index and wherein;

if a single flight configuration satisfies said condition, that the flight phase forms part of said single flight configuration;

if several flight configurations satisfy said condition, that the flight phase forms part of the flight configuration for which the membership function is highest; and

if no flight configuration satisfies said condition, that said flight phase does not form part of any of said defined flight configurations.

9. The process as claimed in claim 8, wherein the coefficient K is equal to 0.85.

10. The process as claimed in claim 8, wherein a flight phase which does not form part of any defined flight configuration is regarded as a new flight configuration used during subsequent applications of said process.

11. The process as claimed in claim 1 wherein at least some of the following flight phases of the aircraft are used as different flight configurations:

takeoff, climb, holding level, banking, descent, approach and landing.

12. The process as claimed claim 1 wherein at least some of the following parameters of the aircraft are used as characteristic parameters to be measured:

load factor, speed, temperature, altitude, yaw sideslip, longitudinal attitude, lateral attitude, angular rate of yaw, flight controls, mass and yaw control.

13. The process as claimed in claim 1, wherein said aircraft is a helicopter and wherein at least some of the following parameters of the helicopter are used as characteristic parameters to be measured:

main rotor speed, rudder bar correction, main rotor power and tail rotor power.

14. The process as claimed in claim 1 wherein a first computer calculates said fuzziness index, wherein a second computer calculates said membership functions, and wherein a central computer linked to said first and second computers determines said flight configuration.