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: An aircraft, missile, projectile, or underwater vehicle with an improved control system, an improved control system, or a method of maneuvering an aircraft, missile, projectile, or underwater vehicle uses control surfaces that are movable along a track. The control system on a track (or “tracked control surface”) advantageously enables the aircraft, missile, projectile, or underwater vehicle to have an unlimited number of configurations, each configuration being tailored to the specific stability or maneuverability requirements during a specific portion of the flight by adjusting the center of pressure of the aircraft, missile, projectile, or underwater vehicle relative to its center of gravity.

Abstract: The present invention relates to an aircraft, missile, projectile or underwater vehicle with an improved control system, an improved control system and a method of maneuvering an aircraft, missile, projectile or underwater vehicle. More particularly, the present invention relates to an aircraft, missile, projectile or underwater vehicle with control surfaces that are movable along a track. The present invention further relates to a method of controlling a aircraft, missile, projectile or underwater vehicle using such a control system. One of the technical advantages of the control system on a track (or “tracked control surface”) over other aircraft, missile, projectile or underwater vehicle control systems is that the tracked control surface system enables the aircraft, missile, projectile or underwater vehicle to have an unlimited number of configurations, each configuration being tailored to the 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 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: An aircraft turret and fairing assembly for facilitating transmission of a directed energy beam from a directed energy device includes a turret section for directing an energy beam. The assembly also includes a fairing section aft of and adjacent to the turret section. Each of the turret section and the aft fairing section are coupled to an aircraft. The assembly also includes at least one sensor for detecting air speed of the aircraft and air pressure. The turret section and the aft fairing section are configured and positioned relative to one another to direct airflow for generating an aeroacoustic resonance within a desired frequency range in an area aft of the turret section.

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.

Abstract: An aircraft turret and fairing assembly for facilitating transmission of a directed energy beam from a directed energy device includes a turret section for directing an energy beam. The assembly also includes a fairing section aft of and adjacent to the turret section. Each of the turret section and the aft fairing section are coupled to an aircraft. The assembly also includes at least one sensor for detecting air speed of the aircraft and air pressure. The turret section and the aft fairing section are configured and positioned relative to one another to direct airflow for generating an aeroacoustic resonance within a desired frequency range in an area aft of the turret section.

Abstract: Apparatus for generating vortices to control the flow of air across a airfoil of an aircraft includes a series of pressure active regions arranged along the leading edge of the airfoil. The pressure active regions include spaced apart valves connected to a source of vacuum, a controller for activating the valves, and sensors for sensing air pressure. The controller is configured to activate the valves in response to the pressure sensed by the sensors, wherein the spaced apart valves are connected to a source of pressurized air as well as to the source of vacuum.