초록 ▼

Disclosed is an airplane all-moving airfoil having a moment reducing apex for facilitating control of the airfoil. In a preferred embodiment, the apex protrudes forward from the leading edge of an all-moving horizontal stabilizer and operates through its aerodynamic effect on the stabilizer to reduc

Disclosed is an airplane all-moving airfoil having a moment reducing apex for facilitating control of the airfoil. In a preferred embodiment, the apex protrudes forward from the leading edge of an all-moving horizontal stabilizer and operates through its aerodynamic effect on the stabilizer to reduce the moment required to maintain and vary the stabilizer position. Counter-rotating airflow vortices produced by the apex reduce the rearward displacement of the center of pressure on the stabilizer as the stabilizer is deflected into an increasing angle of attack. As a result, lighter weight hydraulic stabilizer and elevator actuating mechanisms can be employed. In a preferred embodiment an aeroelastically flexible apex is employed to enhance moment reduction at high angles of attack.

대표청구항 ▼

An all-moving horizontal stabilizer for an aircraft, said stabilizer being rotatable with respect to a fixed portion of the aircraft to which the stabilizer is attached, said stabilizer being rotatable about a control axis extending generally spanwise of the stabilizer from said fixed portion of the

An all-moving horizontal stabilizer for an aircraft, said stabilizer being rotatable with respect to a fixed portion of the aircraft to which the stabilizer is attached, said stabilizer being rotatable about a control axis extending generally spanwise of the stabilizer from said fixed portion of the aircraft, said stabilizer having a leading edge and a moment reducing apex, said apex projecting forwardly from said leading edge to a tip lying generally in the body plane of said stabilizer, said apex being spaced along said leading edge outwardly from said fixed portion of the aircraft to avoid substantial adverse interference effects, said apex having oppositely swept inboard and outboard leading edges mutually converging forwardly toward said tip and spaced apart at said leading edge of said stabilizer by a minor fraction of the spanwise length of said leading edge, said apex having upper and lower apex surfaces which mutually converge spanwise of the stabilizer to said inboard and outboard leading edges of said apex, whereby said apex forms counterrotating airflow vortices to reduce the moment of force required to rotate said stabilizer about said control axis.