Patent ID: 6021977
Filing Date: 2000-02-08
Classification: B64C,Y02T

Abstract:
A stabilizer fin and rudder assembly for an aircraft comprising:a stabilizer fin with airfoil surfaces and with leading and trailing edges;a rudder with a forward margin pivotally mounted on the stabilizer fin trailing edge;the stabilizer fin and rudder assembly being subjected to Bernoulli forces as a relatively moving airstream passes over the assembly in a chordal direction;the stabilizer fin being subjected to crosswind aerodynamic forces due to a crosswind in a direction transverse to the chordal direction; anda pair of fin spoiler means for establishing a lateral force unbalance on the stabilizer fin as the aircraft operates in a crosswind each fin spoiler means having a spoiler with an aerodynamic control surface, a forward margin of the control surface being pivoted on the stabilizer fin on a continuous pivot axis at a chordal location approximately at the stabilizer fin leading edge, one spoiler on each stabilizer fin airfoil surface, each spoiler being pivoted away from the stabilizer fin on the down crosswind side of the stabilizer fin;the fin spoiler having a chordal width of less than 10% of the stabilizer fin and rudder assembly chord whereby effective sideslip capability for the stabilizer fin surfaces, when the aircraft is operated in a crosswind, is substantially increased.