Abstract: In one embodiment, a system includes an aircraft body and a propeller coupled to the aircraft body. The propeller includes a plurality of blades forming a rearward-facing curvature with respect to an axis running longitudinally with the aircraft body. The system further includes a surface coupled to a first blade of the propeller that is operable to reflect radio frequency (RF) waves.

Abstract: In one embodiment, a system includes an aircraft body and a propeller coupled to the aircraft body. The propeller includes a plurality of blades forming a rearward-facing curvature with respect to an axis running longitudinally with the aircraft body. The system further includes a surface coupled to a first blade of the propeller that is operable to reflect radio frequency (RF) waves.

Abstract: The invention reduces the impact of flowfield forces on objects launched from high speed aircraft during flight. For example, the invention provides a solution for overcoming ejection windblast injuries to pilots and increases the probability of injury-free or low-injury ejection. The gas flow is used to rapidly create a very short duration protective “bubble” in the incoming air flow ahead of the ejecting pilot. The bubble reduces the local flow velocity and aerodynamic forces on the pilot during the injury-critical time period of ejection. The invention also is suitable for reducing the intensity of flowfield forces that act on released military aircraft ordnance, such as bombs and missiles.

Abstract: The invention reduces the impact of flowfield forces on objects launched from high speed aircraft during flight. For example, the invention provides a solution for overcoming ejection windblast injuries to pilots and increases the probability of injury-free or low-injury ejection. The gas flow is used to rapidly create a very short duration protective “bubble” in the incoming air flow ahead of the ejecting pilot. The bubble reduces the local flow velocity and aerodynamic forces on the pilot during the injury-critical time period of ejection. The invention also is suitable for reducing the intensity of flowfield forces that act on released military aircraft ordnance, such as bombs and missiles.

Abstract: The present invention provides an exterior skin for a vehicle that includes angularly distributed, individual, fiber-optic elements formed into the exterior skin of a composite, metal, or other material matrix. The vehicle exterior lighting system includes a central light source for providing optical energy of a desired luminescence. A plurality of optical channels of the lighting system transmit the optical energy and are formed from an optically conductive material. The optically conductive material associates through the outer skin of the structural material. The optical channels include terminating ends of the optically conductive material and are essentially flush with the outer skin of the structural material. This permits transmitting the optical energy through the structural material. The invention also includes means for transmitting the optical energy from the central light source to the optical channels.