US 8,265,802 B2 · Method and device for determining the dynamic stability margin of an aircraft

Abstract

A method of determining a dynamic stability margin MSD of an aircraft includes calculating the longitudinal position XMP of a maneuver point MP to find the distance between the maneuver point and the position XCG of the aircraft center of gravity CG, as a function of the angular velocity ωO of an incidence oscillation of the aircraft. A device for determining the dynamic stability margin MSD or a position XMP of the maneuver point MP includes means or acquisition of data and or calculating a dynamic stability margin. The means receive data for generating, the aircraft mass m and pitch inertia Iyy; the flight speed V; the angular velocity ωO of the incidence oscillation at a flight point; a coefficient C*α representing Czα of a “quasi-static” model of the aircraft. The aircraft flight control laws may be adapted according to the stability margin and to XMP.

Claims7

Dependent claims

A method for determining the dynamic stability margin MSD of an aircraft in flight in which a position XMP along a longitudinal X axis of the aircraft of a maneuver point MP is calculated in order to find the distance between said maneuver point and a position XCG along the longitudinal X axis of a center of gravity CG of the aircraft, wherein the position XMP along the longitudinal X axis of said maneuver point MP is determined as a function of an angular velocity ωO of an incidence oscillation of the aircraft, said angular velocity ωO being measured during the flight of the aircraft.

A device able to determine a dynamic stability margin MSD of an aircraft and/or a position XMP along a longitudinal axis of the aircraft, called the X axis, of a maneuver point MP, wherein said device comprises first means of acquisition of data and of calculating the dynamic stability margin MSD, said first means receiving data corresponding to or sufficient for generating:

a current mass m of the aircraft;
a current inertia Iyy of the aircraft about an axis of rotation in pitch, parallel with an axis Y of the aircraft reference system perpendicular to a vertical plane of symmetry of the aircraft;
a current true aerodynamic speed V of the aircraft at the flight point in question;
an angular velocity ωO of an incidence oscillation of the aircraft at the flight point in question;
a coefficient C*α of a status matrix [A] of a “quasi-static” model of the aircraft.

2 more elements

Dependencies are inferred from the claim text.

Method and device for determining the dynamic stability margin of an aircraft

Life of this patent

Method and device for determining the dynamic stability margin of an aircraft

Life of this patent

Abstract

Claims7