Abstract: An auxiliary flaperon control is pivotally mounted on the trailing edge of each wing of an aircraft between the outboard control surfaces and the fuselage and in close proximity to the tail of said aircraft; the auxiliary flaperon controls being operable relative to the outboard control surfaces to induce supplementary aerodynamic forces on the aircraft tail to thereby augment the effectiveness of aircraft lateral and directional control.

Abstract: Vane members are movably mounted on the hulls of watercraft to serve steering and stabilization functions. Several embodiments are provided, some of which rotate between extended and shielded positions, others of which fold to vary the angle at which they extend from their associated hull, and still others of which both rotate and fold to facilitate storage alongside planar hull portions. Both shaft and surface bearing vane mounting systems are described. In preferred practice, the vanes are used on hydrofoil-carrying semi-displacement ships, and the provision of stowably mounted hydrofoils, planing surfaces, and wave form generators on such ships is also provided. Such vane members are also provided on vehicles operable in a fluid medium, such as torpedos operable completely submerged in water, and aerial vehicles such as missiles and aircraft of both the rotary wing and fixed wing types, to similarly serve steering and stabilization functions.

Abstract: A wing, for aircraft of cropped, arrow-type planform with thin leading and side edges, having a pivotable tip to alter the crop angle of the wing during flight. Increasing the crop angle causes the wing side edge to become a trailing edge which reduces the strength of the side edge vortex flow. Decreasing the crop angle causes opposite results, in particular the side edge is now a leading edge and can generate a leading edge vortex flow. The wing constitutes a roll control device for aircraft of the stated design particularly effective at higher angles of attack.

Abstract: A free wing attached to a fuselage of an aircraft in a manner such that the wing is free to pivot about a spanwise axis forward of its aerodynamic center. The wing is angularly displaced about the axis by aerodynamic pitching moments, resulting from lift, and is trimmed through a use of a trimmable free stabilizer comprising a floating canard mounted on a strut rigidly connected to the wing and forwardly projected therefrom.

Abstract: A foil for a hydrofoil comprises a rigid part and a deformable trailing or leading edge part. The deformable part comprises a movable core jointed to the foil proper and having a resilient layer deposited on it, the resilient layer providing continuity of profile between the rigid and the deformable part.

Abstract: An electrical system for actuating the inboard spoilers on the wings of an aircraft in response to the lateral control input from the pilot control wheel and to the position of the pilot speed brake lever. The pilot speed brake lever position signal being used to select the modulation provided by a three mode function generator which generates the signal that actuates the spoilers.

Abstract: An aircraft forwardly propelled by a power plant including a pair of jet engines, is operated in a VTOL mode by powered rotation of a rotary wing mechanically rotoring the engines. When unloaded during fixed wing flight, the power plant is operated in an accelerating rocket mode preceding high speed ram jet operation. Radially extensible blades of the rotary wing vary the mechanical loading on the engines while adjustable chokes at the intake of each engine and in the outlet of a common after-burner for the engines, condition the power plant for its different operational modes.

Abstract: This invention relates to the arrangement of lifting, stabilizing, and flight controlling, wing surfaces, placed near the front of an aircraft, with main lifting wing surfaces, placed toward the rear. Control surfaces placed rearwardly on the aft fuselage and/or the rear main lifting wing surfaces, are also indicated.