Abstract: A forebody flow control system and more particularly an aircraft or missile flow control system for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one deployable flow effector on the missile or aircraft forebody; at least one sensors each having a signal associated therewith, the at least one sensor being used for determining or estimating flow separation or side forces on the missile forebody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one deployable flow effector based on at least in part the signal of the at least one sensor.

Abstract: The present invention relates, in general, to pressure sensors capable of operating at high temperatures. The present invention further relates to a high temperature pressure sensor with an improved gage factor. The present invention still further provides a pressure sensor with a smaller sized diaphragm, which is capable of reading higher pressures. The present invention also provides a method and sensor for detecting strain using shape memory alloys.

Abstract: The present invention relates, in general, to pressure sensors capable of operating at high temperatures. The present invention further relates to a high temperature pressure sensor with an improved gage factor. The present invention still further provides a pressure sensor with a smaller sized diaphragm, which is capable of reading higher pressures. The present invention also provides a method and sensor for detecting strain using shape memory alloys.

Abstract: A forebody flow control system and more particularly to aircraft or missile flow control systems for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one flow effector on the missile or aircraft forebody; at least one sensor having a signal associated therewith, the at least one sensor being positioned to detect flow separation on the missile or aircraft forebody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one flow effector based on at least in part the signal of the at least one sensor.

Abstract: The present invention relates, in general, to pressure sensors capable of operating at high temperatures. The present invention further relates to a high temperature pressure sensor with an improved gage factor. The present invention still further provides a pressure sensor with a smaller sized diaphragm, which is capable of reading higher pressures. The present invention also provides a method and sensor for detecting strain using shape memory alloys.

Abstract: The present invention relates to a watercraft with an improved waterjet propulsion system. The present invention further relates to a waterjet propulsion system with an improved steering nozzle design. The watercraft preferably is either what is known as a jet ski, a boat or a ship. A watercraft can be propelled by the thrust produced by a high-speed waterjet discharged from a nozzle located at the rear of the watercraft. A device that enables this type of propulsion is called a waterjet propulsor or a propulsor. Larger watercraft, such as a boat or a ship may often have two or more waterjet propulsors. The improved steering nozzle design incorporates a groove(s) or a channel(s) that is formed or machined into the steering nozzle wall thickness and does not exceed the thickness of the wall. The groove(s) or channel(s) begins at a point between the steering nozzle inlet and exit and ends at a point near or at the exit of the steering nozzle.

Abstract: The present invention relates to a flow control device and more particularly to reactive self-contained modular flow control device with deployable flow effectors. The present invention further relates to a method of operating the flow control device. One embodiment of the present invention includes a method of controlling air flow across a surface of an aircraft under certain flight conditions comprising the steps of sensing fluid separation from the surface by measuring the pressure on the surface; determining a standard deviation of the pressure measurements over a period of time; and deploying a flow effector in response to the standard deviation of the pressure measurements exceeding a predetermined threshold number.

Abstract: The present invention relates to a forebody flow control system and more particularly to aircraft or missile flow control system for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one deployable flow effector on the missile or aircraft forebody; at least one sensors each having a signal, the at least one sensor being positioned to detect flow separation on the missile or aircraft forebody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one deployable flow effector based on at least in part the signal of the at least one sensor.

Abstract: The present invention relates to a flow control device and more particularly to reactive modular flow control device with deployable flow effectors. The present invention further relates to a method of operating the flow control device. One embodiment of the present invention includes a method of controlling air flow across a surface of an aircraft under certain flight conditions comprising the steps of sensing fluid separation from the surface by measuring the pressure on the surface; determining a standard deviation of the pressure measurements over a period of time; and deploying a flow of effector in response to the standard deviation of the pressure measurements exceeding a predetermined threshold number.

Abstract: The present invention relates to a flow control device and more particularly to reactive modular flow control device with deployable flow effectors. The present invention further relates to a method of operating the flow control device.

Abstract: The present invention relates to a forebody flow control system and more particularly to aircraft or missile flow control system for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one deployable flow effector on the missile or aircraft forebody; at least one sensors each having a signal, the at least one sensor being positioned to detect flow separation on the missile or aircraft forebody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one deployable flow effector based on at least in part the signal of the at least one sensor.