Abstract A delta-wing aircraft comprises a pair of auxiliary wings pivotably mounted forwardly of the leading edge of the delta-wing from a deployed position at lower speeds wherein they increase lift and also act as horizontal stabilizers, to a retracted dragdecreasing position at cruising speeds. In one described embodiment, the auxiliary wings are pivotable about a vertical axis of the aircraft from a deployed position wherein their leading edges are about 90* to the longitudinal axis of the aircraft, to a retracted position wherein they form the apex of the delta-wing; in both positions, the mean aerodynamic chord of the auxiliary wings is aligned with that of the delta-wing. In a second described embodiment, the pair of auxiliary wings are pivoted about a horizontal axis of the aircraft, from a deployed position substantially perpendicular to the longitudinal axis of the aircraft, to a retracted position substantially flush with the aircraft fuselage.
An aircraft comprising a fuselage and a main delta wing fixed to the fuselage, characterized in that the aircraft includes a pair of auxiliary wings each pivotably mounted about a vertical axis at the forward juncture of the main delta wing with the fuselage, said auxiliary wings being pivotable from a deployed position at lower speeds to a retracted position at cruising speed and constituting the apex of the main delta wing when in said retracted position, the mean aerodynamic chord of said auxiliary wings being in alignment with that of the main delta wing in both the deployed and retracted positions of said auxiliary wings, said auxiliary wings when in said deployed position, increasing the total surface area, aspect ratio, camber, and effective thickness of the total wing surface area including the main delta wing and the auxiliary wings, thereby increasing lift and horizontal stabilization of the aircraft.
Claim 2
Dependent Claim
149 words
An aircraft comprising a fuselage and a main delta wing fixed to the fuselage, characterized in that the aircraft includes a pair of auxiliary wings each pivotably mounted about a vertical axis at the forward juncture of the main delta wing with the fuselage, said auxiliary wings being pivotable from a deployed position at lower speeds to a retracted position at cruising speed and constituting the apex of the main delta wing when in said retracted position, the mean aerodynamic chord of said auxiliary wings being in alignment with that of the main delta wing in both the deployed and retracted positions of said auxiliary wings, said auxiliary wings when in said deployed position, increasing the total surface area, aspect ratio, camber, and effective thickness of the total wing surface area including the main delta wing and the auxiliary wings, thereby increasing lift and horizontal stabilization of the aircraft.
Claim 3
Dependent Claim
30 words
An aircraft as defined in claim 1, wherein the surface area of said pair of auxiliary wings constitute about 10-20 percent of the surface area of the main delta wing.
Claim 4
Dependent Claim
18 words
The aircraft as defined in claim 1, wherein said auxiliary wings carry control flaps at their trailing edges.
Claim 5
Dependent Claim
39 words
The aircraft as defined in claim 1, wherein said auxiliary wings may be pivoted to a fully deployed position so that their leading edges form an angle of at least about 90* to the longitudinal axis of the aircraft.