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Process and system for determining the longitudinal position of the center of gravity of an aircraft provided with an adjustable horizontal stabilizer and application to the monitoring of said center of gravity near the focus of the aircraft
| Details |
Inventors: Buisson, Dominique; Moline, Augustin;
Assignee: Aerospatiale Societe Nationale Industrielle (Paris, FR)
Primary Examiner: Chin; Gary
Assistant Examiner:
Attorney, Agent or Firm: Fisher, Christen & Sabol
Method and system for determining the longitudinal position of the gravity center of an aircraft provided with an adjustable stabilizer. At a point of flight for which the aircraft is in equilibrium with its elevator in aerodynamic prolongation of the adjustable stabilizer and when the gravity center is at the vicinity of the focus of the aircraft, the gravity center position is calculated from: the position (X.sub.F) of the focus (F) of the aircraft, the measurement of the deflection (iH) of the adjustable stabilizer, a first function K(M, N1) of the engine speed (N1) of the engines of the aircraft and the Mach number (M); and a second function of such Mach number. There is application to the monitoring of the gravity center of a flying aircraft. |
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DETAILED DESCRIPTION The object of the present invention is a reliable and precise process for determining the longitudinal position of the centre of gravity of an aircraft near the focus and, more particularly, a monitoring system completely independent of the fuel regulating system, allowing a detection of breakdowns which could not be seen by the monitorings of said regulation system, whilst making it possible to multiply the probabilities of breakdown detection and thus to ensure overall security.
To that end, according to the invention, the process for determining the longitudinal position of the centre of gravity of an aircraft provided with an adjustable horizontal stabilizer, is noteworthy in that, at a point of flight for which said aircraft is in equilibrium with its elevator in aerodynamic extension of said adjustable horizontal stabilizer and when said centre of gravity lies near the focus of said aircraft, said position of the centre of gravity is calculated from: the position of the focus of said aircraft; the measurement of the deflection of said adjustable horizontal stabilizer; a first function of the speed of the aircraft engines and of the Mach number, this first function being representative of the value of deflection of said adjustable horizontal stabilizer, in the case of said centre of gravity being located at the focus of said aircraft; and a second function of said Mach number, this second function being representative of the deviation of deflection of said horizontal stabilizer for a deviation of 1% from the position of the centre of gravity.
As will be seen in greater detail hereinafter, the present invention takes advantage of the fact that the deflection of the adjustable horizontal stabilizer, when the aircraft is trimmed, i.
e.
when the equilibrium in pitch moment is effected and the elevator presents a zero angle of incidence with respect to said stabilizer, is a function of the flight conditions and of the position of the centre of gravity of the aircraft
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Navigation and GPS 
