Abstract: The composite structural panel has bottom, top and edge layers which enclose a primary core. The core provides additional structural strength to the panel. The edge layer forms a desired panel edge angle of approximately 20.degree. to 45.degree.. The primary core is trimmed at an angle of approximately one-half the desired edge angle to form a first pressure reaction surface. A peripheral core is positioned on the tapered portion of the primary core so that the axis of the peripheral core is perpendicular to the first pressure reaction surface. The peripheral core is trimmed to form a second pressure reaction surface beneath the edge of the panel. The structure is lightweight and resists deformation of the panel edge when the panel is cured under elevated pressure in an autoclave.

Abstract: A varied thickness laminate or panel (92, 128) is fabricated by polar winding incomplete lamina or plies (54, 146, 148) on a mandrel (10, 110, 130) at selected angles. The plies (54) are wound at crossing angles, first one layer (60) at one angle and then a second layer (64) at a second angle. At the most remote crossing point from a wide starting end (32), a V (66) is formed between the crossing plies (60, 64) and in the space (62) formed by the V (66), no plies extend on the mandrel side (30). Thus, the winding on each side (30) is incomplete, a space (62) between successive V's (66, 154, 164, 174) being skipped by steps of the crossing plies. The first V (66) starts a taper from wide starting end (32) to narrow other end (34). Successive plies are wound around the mandrel from the polar ends (48, 50, 134), each successive set forming a V so as to thicken the windings in steps formed by the V's.

Abstract: A varied thickness laminate or panel (92, 128) is fabricated by polar winding incomplete lamina or plies (54, 146, 148) on a mandrel (10, 110, 130) at selected angles. The plies (54) are wound at crossing angles, first one layer (60) at one angle and then a second layer (64) at a second angle. At the most remote crossing point from a wide starting end (32), a V (66) is formed between the crossing plies (60, 64) and in the space (62) formed by the V (66), no plies extend on the mandrel side (30). Thus, the winding on each side (30) is incomplete, a space (62) between successive V's (66, 154, 164, 174) being skipped by steps of the crossing plies. The first V (66) starts a taper from wide starting end (32) to narrow other end (34). Successive plies are wound around the mandrel from the polar ends (48, 50, 134), each successive set forming a V so as to thicken the windings in steps formed by the V's.

Abstract: An actuating mechanism for variable camber leading edges of aerodynamic airfoils characterized by its rigidity and structural stability and which permits varying the camber of a flexible continuous airfoil skin through leading edge deflection angles ranging from on the order of 14.degree. to on the order of 22.degree. with reference to the wing box chord line without deployment of a Krueger flap and up to on the order of 32.degree.

Abstract: A varied thickness laminate or panel (92, 128) is fabricated by polar winding incomplete lamina or plies (54, 146, 148) on a mandrel (10, 110, 130) at selected angles. The plies (54) are wound at crossing angles, first one layer (60) at one angle and then a second layer (64) at a second angle. At the most remote crossing point from a wide starting end (32), a V (66) is formed between the crossing plies (60, 64) and in the space (62) formed by the V (66), no plies extend on the mandrel side (30). Thus, the winding on each side (30) is incomplete, a space (62) between successive V's (66, 154, 164, 174) being skipped by steps of the crossing plies. The first V (66) starts a taper from wide starting end (32) to narrow other end (34). Successive plies are wound around the mandrel from the polar ends (48, 50, 134), each successive set forming a V so as to thicken the windings in steps formed by the V's.

Abstract: An airfoil having a support frame, a trailing edge end section, and upper and lower variable camber skin sections extending rearwardly from the support frame to the trailing edge end section. A walking beam is positioned between the upper and lower variable camber skin sections, and comprises a forward positioning section and a rearwardly extending locating arm. The positioning section is connected to the lower swing ends of two pivot links in a manner that forward or rearward movement of the positioning section causes the locating arm of the walking beam to rotate, respectively, downwardly or upwardly. A whiffle tree beam is connected by its forward end to the support frame and by its rear end is pivotally connected to the trailing edge end section, with the whiffle tree beam being connected at an intermediate portion thereof to the rear end of the locating arm of the walking beam. A tilting arm is connected to the locating arm, to the whiffle tree beam and to the trailing edge section.

Abstract: A variable camber leading edge airfoil system that is attached to the front f the fixed wing section of an aircraft. When the system is in the retracted position it provides an airfoil having a slight curvature suitable for supersonic flight and when in the extended position it provides an airfoil having a large curvature suitable for high lift subsonic flight. The system is capable of operating at any intermediate position depending upon the requirements of any particular flight conditions. The system includes a rigid lower panel, a leading edge beam, a flexible upper panel and an actuating mechanism. Actuation of the actuating mechanism to the extended position simultaneously causes the rigid lower panel to move downward and rotate counterclockwise, the leading edge beam to move downward and rotate counterclockwise, and causes the flexible upper panel to flex to a proper curvature and have the rearward edge move forward and slide along the upper forward edge of the fixed wing section.