초록 ▼

Aerodynamic control apparatus for an aircraft is provided which includes a pair of control surfaces, one for each side of the aircraft, each control surface extending between a root end at the fuselage and a distant tip end. The root end of each control surface is pivotally mounted on the fuselage o

Aerodynamic control apparatus for an aircraft is provided which includes a pair of control surfaces, one for each side of the aircraft, each control surface extending between a root end at the fuselage and a distant tip end. The root end of each control surface is pivotally mounted on the fuselage on a stationary hinge axis which is angularly disposed relative to the longitudinal axis of the aircraft. The hinge axis is elevated or depressed at the leading edge of the control surface relative to the trailing edge such that the hinge axis is in an oblique orientation relative to the longitudinal axis of the aircraft. An actuator enables selective movement of each control surface to any one of a range of positions between an inactive position flush with a contoured outer surface of the fuselage and a deployed position at which a tip end of the control surface is distant from the fuselage. In one instance, the control surfaces can be simultaneously moved about their associated hinge axis on both sides of the fuselage to achieve pitch control of the aircraft. In other instances, only the control surface on one side is moved about its hinge axis to achieve either yaw control or roll control. In another embodiment, the control surfaces are mounted on hinge arms which offset the control surfaces from the fuselage to provide an air gap between control surface and fuselage.

대표청구항 ▼

In combination with an aircraft including a fuselage having a nose, a tail, and a longitudinal axis extending between said nose and said tail, aerodynamic control apparatus comprising: a control surface extending between a root end and a tip end distant from said root end and between a leading edge

In combination with an aircraft including a fuselage having a nose, a tail, and a longitudinal axis extending between said nose and said tail, aerodynamic control apparatus comprising: a control surface extending between a root end and a tip end distant from said root end and between a leading edge generally facing in the direction of said nose and a trailing edge generally facing in the direction of said tail; and means mounting said root end of said control surface on said fuselage for single degree of freedom pivotable movement on a stationary hinge axis which is angularly disposed relative to said longitudinal axis, said hinge axis extending in an oblique orientation relative to said longitudinal axis, said hinge axis and said longitudinal axis being axially divergent each from the other.