Abstract: A projectile incorporates one or more spoiler-tabbed spinning disks to effect flow around the projectile and thus impart steering forces and/or moments. The spoiler tabs may be deployed only during steering phases of travel thus minimizing the drag penalty associated with steering systems. The disks are driven by motors and informed and controlled by sensors and electronic control systems. The spoiler tabs protrude through the surface of the projectile only for certain angles of spin of the spinning disk. For spin-stabilized projectiles, the disks spin at substantially the same rate as the projectile, but the disks may function in fin-stabilized projectiles as well. Any number of such spinning flow effector disks may be incorporated in a projectile, with the manner of functional coordination differing slightly for even and odd numbers of disks.

Abstract: A projectile incorporates one or more spoiler-tabbed spinning disks to effect flow around the projectile and thus impart steering forces and/or moments. The spoiler tabs may be deployed only during steering phases of travel thus minimizing the drag penalty associated with steering systems. The disks are driven by motors and informed and controlled by sensors and electronic control systems. The spoiler tabs protrude through the surface of the projectile only for certain angles of spin of the spinning disk. For spin-stabilized projectiles, the disks spin at substantially the same rate as the projectile, but the disks may function in fin-stabilized projectiles as well. Any number of such spinning flow effector disks may be incorporated in a projectile, with the manner of functional coordination differing slightly for even and odd numbers of disks.

Abstract: A projectile incorporates one or more spoiler-tabbed spinning disks to effect flow around the projectile and thus impart steering forces and/or moments. The spoiler tabs may be deployed only during steering phases of travel thus minimizing the drag penalty associated with steering systems. The disks are driven by motors and informed and controlled by sensors and electronic control systems. The spoiler tabs protrude through the surface of the projectile only for certain angles of spin of the spinning disk. For spin-stabilized projectiles, the disks spin at substantially the same rate as the projectile, but the disks may function in fin-stabilized projectiles as well. Any number of such spinning flow effector disks may be incorporated in a projectile, with the manner of functional coordination differing slightly for even and odd numbers of disks.

Abstract: A projectile incorporates one or more spoiler-tabbed spinning disks to effect flow around the projectile and thus impart steering forces and/or moments. The spoiler tabs may be deployed only during steering phases of travel thus minimizing the drag penalty associated with steering systems. The disks are driven by motors and informed and controlled by sensors and electronic control systems. The spoiler tabs protrude through the surface of the projectile only for certain angles of spin of the spinning disk. For spin-stabilized projectiles, the disks spin at substantially the same rate as the projectile, but the disks may function in fin-stabilized projectiles as well. Any number of such spinning flow effector disks may be incorporated in a projectile, with the manner of functional coordination differing slightly for even and odd numbers of disks.

Abstract: Multiple redundant harmonic drive motors on a rotor head actuate the angle of attack of rotor blades at the rotor blade roots, providing collective control that, in combination with a system for providing cyclic control on the rotor blades, eliminates the need for a swashplate, thereby advantageously reducing the weight and maintenance cost of a helicopter, increasing its reliability, and reducing its vulnerability to ballistic attack.

Abstract: A projectile incorporates one or more spoiler-tabbed spinning disks to effect flow around the projectile and thus impart steering forces and/or moments. The spoiler tabs may be deployed only during steering phases of travel thus minimizing the drag penalty associated with steering systems. The disks are driven by motors and informed and controlled by sensors and electronic control systems. The spoiler tabs protrude through the surface of the projectile only for certain angles of spin of the spinning disk. For spin-stabilized projectiles, the disks spin at substantially the same rate as the projectile, but the disks may function in fin-stabilized projectiles as well. Any number of such spinning flow effector disks may be incorporated in a projectile, with the manner of functional coordination differing slightly for even and odd numbers of disks.

Abstract: The present invention relates to an aircraft, missile, projectile, or underwater vehicle with an improved control system and a method for increasing the maneuverability or stability of an aircraft, missile, projectile, or underwater vehicle. More particularly, the present invention relates to a method for increasing the maneuverability or stability of an aircraft, missile, underwater vehicle or projectile through the use of removable control surfaces. The technical advantage of the removable control surface system (or “removable control surface”) over other systems is that the removable control surface system enables the aircraft, missile, underwater vehicle or projectile to have two or more design configurations, each configuration being tailored to the aircraft, missile, projectile, or underwater vehicle's specific stability or maneuverability requirements during a specific portion of the flight.

Abstract: A forebody flow control system and more particularly an aircraft or missile flow control system for enhanced maneuverability and stabilization utilizes various types of sensors and various types of activatable flow effectors to maneuver the aircraft or missile with the help of a control system. A method of operating the flow control system is also disclosed.

Abstract: The present invention relates to an aircraft, missile, projectile, or underwater vehicle with an improved control system and a method for increasing the maneuverability or stability of an aircraft, missile, projectile, or underwater vehicle. More particularly, the present invention relates to a method for increasing the maneuverability or stability of an aircraft, missile, underwater vehicle or projectile through the use of removable control surfaces. The technical advantage of the removable control surface system (or “removable control surface”) over other systems is that the removable control surface system enables the aircraft, missile, underwater vehicle or projectile to have two or more design configurations, each configuration being tailored to the aircraft, missile, projectile, or underwater vehicle's specific stability or maneuverability requirements during a specific portion of the flight.

Abstract: A helicopter uses multiple redundant harmonic drive motors on the rotor head to actuate the angle of attack of rotor blades at the rotor blade roots, providing collective control that, in combination with a system for providing cyclic control on the rotor blades, eliminates the need for a swashplate, thereby advantageously reducing the weight and maintenance cost of the helicopter, increasing its reliability, and reducing its vulnerability to ballistic attack.

Abstract: The present invention relates to an aircraft, missile, projectile, or underwater vehicle with an improved control system and an improved control system for maneuvering an aircraft, missile, projectile, or underwater vehicle. More particularly, the present invention relates to an aircraft, missile, underwater vehicle or projectile with removable control surfaces. The technical advantage of the removable control surface system (or “removable control surface”) over other systems is that the removable control surface system enables the aircraft, missile, underwater vehicle or projectile to have two or more design configurations, each configuration being tailored to the aircraft, missile, projectile, or underwater vehicle's specific stability or maneuverability requirements during a specific portion of the flight.

Abstract: The present invention relates to an aircraft, missile, projectile, or underwater vehicle with an improved control system and an improved control system for maneuvering an aircraft, missile, projectile, or underwater vehicle. More particularly, the present invention relates to an aircraft, missile, underwater vehicle or projectile with removable control surfaces. The technical advantage of the removable control surface system (or “removable control surface”) over other systems is that the removable control surface system enables the aircraft, missile, underwater vehicle or projectile to have two or more design configurations, each configuration being tailored to the aircraft, missile, projectile, or underwater vehicle's specific stability or maneuverability requirements during a specific portion of the flight.