Method for improving roll steering of an aircraft and aircraft using same
View Patent ↗A roll steering method subdivides the direction of an aircraft control surface into two elements and, during a roll control operation using ailerons, steers an upper element of the control surface in the roll direction and a lower element in the opposite direction.
1. A method for improving the roll steering of an aircraft of large dimensions comprising:
a fuselage,
two wings symmetric with respect to said fuselage, provided with controllable aerodynamic surfaces configured to produce a roll movement for the aircraft, and
a vertical fin projecting upwards with respect to the rear part of said fuselage and provided with a rudder extending along the rear edge of said fin and configured to turn, with respect to said vertical fin, about an axis of rotation,
said method comprising:
dividing said rudder, transversely to said axis of rotation, into at least two individual rudder elements disposed successively along said axis of rotation and being independently controllable in rotation about said axis of rotation, and
when said wing aerodynamic surfaces are deflected so as to communicate a roll movement to said aircraft in a determined direction:
deflecting at least one of said individual rudder elements disposed farther from said fuselage in said determined direction of roll, and
simultaneously, deflecting at least one of said individual rudder elements disposed nearer to said fuselage in the opposite direction.
2. The method as claimed in claim 1 , wherein the antagonistic yaw effects produced by the rudder elements deflected in opposite directions balance one another at least approximately.
3. The method as claimed in claim 1 , wherein:
said rudder is divided into a lower rudder element and into an upper rudder element; and
during a roll movement produced by said aerodynamic surfaces of the wings, said upper rudder element is deflected in the direction of said roll movement and said lower rudder element is deflected in the opposite direction simultaneously.
4. The method as claimed in claim 3 , wherein the surface areas of said lower and upper rudder elements are at least approximately equal and said lower and upper rudder elements are deflected symmetrically about said axis of rotation of said rudder.
5. The method as claimed in claim 1 , wherein the deflection of said rudder elements is subject to the exceeding of a threshold by a parameter representative of a particular flight situation of said aircraft.
6. The method as claimed in claim 5 , wherein said parameter is the speed of the aircraft.
7. The method as claimed in claim 5 , wherein said parameter is the Mach number.
8. The method as claimed in claim 5 , wherein said parameter is the dynamic pressure.
9. An aircraft with improved roll control implementing the method specified under claim 2 , comprising:
a fuselage;
two wings, symmetric with respect to said fuselage, provided with controllable aerodynamic surfaces configured to produce a roll movement for the aircraft;
a roll steering unit that roll steers said aircraft operable to control said controllable aerodynamic surfaces;
a vertical fin projecting with respect to the rear part of said fuselage and provided with a rudder extending along the rear edge of said fin and configured to turn, with respect to the latter, about an axis of rotation; and
a yaw steering unit that yaw steers said aircraft operable to control said rudder,
wherein:
said rudder comprises at least two rudder elements disposed successively along said axis of rotation;
said yaw steering unit is configured to produce first individual deflection orders for each of said rudder elements;
said roll steering unit is configured to produce, in addition to deflection orders for said aerodynamic surfaces, second individual deflection orders for said rudder elements, said second deflection orders being such that the resultant yaw action is at least approximately zero; and
an addition unit is provided for adding, for each of said rudder elements, the second individual deflection order to the corresponding first individual deflection order when the measurement of a parameter representative of a particular flight situation exceeds a preset threshold.
10. The aircraft as claimed in claim 9 , wherein said rudder comprises a lower rudder element and an upper rudder element.