Double-pivoting deployment system for aerosurfaces

In combination with a support structure of an aerospace vehicle, and aerosurface deployment assembly, comprising:

• (a) an actuating means;
• (b) a plurality of aerosurfaces, each having an inner segment and an outer segment, wherein each said inner segment is pivotally connected to said support structure at an axis of rotation substantially perpendicular to the longitudinal axis of the aerospace vehicle, and wherein an outer side portion of each said inner segment is pivotally connected to an inner side portion of each said outer segment at an axis of rotation parallel to said longitudinal axis when said aerosurfaces are in the stowed position, wherein each said outer segment of said aerosurface comprises a forward curved portion, and wherein said support structure comprises a curved guide portion, said forward curved portion being capable of travel along said curved guide portion;
• (c) a yoke means, operably connected to said actuating means, for translational travel along said support structure;
• and
• (d) a plurality of linkage rods for interconnecting said yoke means and said aerosurfaces, wherein a single linkage rod interconnects said yoke to each said aerosurface, and wherein translational travel of said yoke means, initiated by said actuating means, moves said plurality of linkage rods to rotate said aerosurfaces about each of said axes of rotation substantially perpendicular to said longitudinal axis and each of said axes of rotation parallel to said longitudinal axis thereby deploying said aerosurfaces.

In combination with a support structure of an aerospace vehicle, an aerosurface deployment assembly, comprising:

• (a) an actuating means;
• (b) a plurality of aerosurfaces, each having an inner segment and an outer segment, wherein each said inner segment is pivotally connected to said support structure at an axis of rotation substantially perpendicular to the longitudinal axis of the aerospace vehicle, and wherein an outer side portion of each said inner segment is pivotally connected to an inner side portion of each said outer segment at an axis of rotation parallel to said longitudinal axis when said aerosurfaces are in the stowed position;
• (c) a yoke means, operably connected to said actuating means, wherein a pushrod connects said yoke means to said actuating means for translational travel along said support structure;
• and
• (d) a plurality of linkage rods for interconnecting said yoke means and said aerosurfaces, wherein a single linkage rod interconnects said yoke to each said aerosurface, and
• wherein translational travel of said yoke means, initiated by said actuating means, moves said plurality of linkage rods to rotate said aerosurfaces about each of said axes of rotation substantially perpendicular to said longitudinal axis and each of said axes of rotation parallel to said longitudinal axis thereby deploying said aerosurfaces.