Aerodynamic re-entry vehicle control with active and passive yaw flaps

A yaw control system for a hypersonic, re-entry vehicle, comprising:

• at least two movable yaw control surfaces arranged on generally opposite sides of the vehicle, each said movable yaw control surface being capable of moving independently of the other between at least one extended position that operates to apply a turning moment to the vehicle, and a retracted position;
• and
• two pairs of fixed yaw control surfaces that each border opposite sides of a respective one of the movable yaw control surfaces and that project outwardly from an outer surface of a body of the vehicle;
• each said pair of fixed yaw control surfaces together with its respective said movable yaw control surface, when said movable yaw control surface is in its retracted position, providing passive yaw stabilization for maneuvering when entering a planetary atmosphere;
• and
• wherein the fixed yaw control surfaces operate to shield the movable yaw control surfaces from erosion resulting from entry into the planetary atmosphere, such that substantially all of each of the movable yaw control surfaces are preserved.

A hypersonic vehicle comprising:

• a body having an outer surface defining a generally tapered conical shape;
• at least two movable yaw control surfaces arranged at spaced apart locations on said body, with each said movable yaw control surface being moveable between an extended position that operates to apply a turning moment to the body during flight of the vehicle, and a retracted position;
• and
• a pair of fixed yaw control surfaces associated with each one of said movable yaw control surfaces, each said pair of fixed yaw control surfaces being positioned adjacent to the sides of an associated one of said movable yaw control surfaces and projecting from said outer surface of said body;
• when each of said movable yaw control surfaces is in said retracted position, its respective pair of fixed yaw control surfaces provide passive yaw stabilization for the vehicle during flight of the vehicle;
• and
• each said pair of fixed yaw control surfaces adapted to shield side portions of its associated said movable yaw control surface from erosion resulting from heat generation during entry into a planetary atmosphere.

A method for controlling the operation of a hypersonic vehicle having at least one movable control surface, the method comprising:

• using at least a pair of fixed control surfaces disposed closely adjacent to side portions of the at least one movable control surface to cover the side portions of the at least one movable control surface when the at least one movable control surface is in a retracted position, the fixed control surfaces projecting from an outer surface of the vehicle and assisting in providing yaw control of the vehicle;
• maintaining the at least one movable control surface in a stowed position, in which the at least one movable control surface is generally flush with the adjacent fixed control surface, until the vehicle has completed entry into the earth's atmosphere;
• and
• subsequently controlling the extension and retraction of the at least one movable control surface as needed to provide skid-to-turn maneuvering for guiding the vehicle towards a target.