Abstract: A method for sending messages through the atmosphere. The method includes sending the messages to an intended recipient, such as an aircraft, on a data link over an operating frequency at or near an atmospheric absorption band, where the operating frequency is selected to be closer to or farther from the absorption band to control the attenuation of the messages in the atmosphere so that the intended recipient is able to receive the messages, but unintended recipients are unable to receive the messages or jamming signals are unable to jam the messages.

Abstract: A system and method for controlling a swarm of UAVs that are stored on and released from an airborne platform, fly to and destroy a target, where the UAVs download target information from the airborne platform before being released therefrom, do not communicate with each other or the airborne platform while in flight, and do not depend of the presence of GPS. Each UAV includes a vision sensor that provides image data, a navigation module that receives the image data and causes the UAV to navigate and fly towards the target, and a target destruction module that receives the image data and causes the UAV to destroy the target.

Abstract: A method for detecting defects in a composite structure, such as in an aircraft structure, that includes sending an optical signal down an optical fiber embedded in the composite structure and analyzing the optical signal at a detector. If it is determined that the optical signal is turning on and off or an increase in the bit error rate is occurring at the detector, the composite structure may be delaminating or the composite structure may be somehow damaged. If it is determined that the composite structure is damaged, the optical signal can be sent down a different optical fiber that may not be at a location where the composite structure is damaged, and a continuous beam of light can be sent down the optical fiber that is at the damaged part of the composite structure to determine whether the damage is increasing.

Abstract: A system and method for controlling a swarm of UAVs that are stored on and released from an airborne platform, fly to and destroy a target, where the UAVs download target information from the airborne platform before being released therefrom, do not communicate with each other or the airborne platform while in flight, and do not depend of the presence of GPS. Each UAV includes a vision sensor that provides image data, a navigation module that receives the image data and causes the UAV to navigate and fly towards the target, and a target destruction module that receives the image data and causes the UAV to destroy the target.

Abstract: A method for detecting defects in a composite structure, such as in an aircraft structure, that includes sending an optical signal down an optical fiber embedded in the composite structure and analyzing the optical signal at a detector. If it is determined that the optical signal is turning on and off or an increase in the bit error rate is occurring at the detector, the composite structure may be delaminating or the composite structure may be somehow damaged. If it is determined that the composite structure is damaged, the optical signal can be sent down a different optical fiber that may not be at a location where the composite structure is damaged, and a continuous beam of light can be sent down the optical fiber that is at the damaged part of the composite structure to determine whether the damage is increasing.

Abstract: A manned aircraft and unmanned aerial vehicles (UAVs) fly on a mission as a team. The UAVs carry additional weapons and/or munitions that can be controlled by the manned aircraft. The pilot of the manned aircraft selects weapons or munitions carried by either the manned aircraft or one of the UAVs. A display in the manned aircraft illustrates weapons available on both the manned aircraft and UAVs. The pilot of the manned aircraft picks a weapon from the display and then targets and fires the weapon. The targeting and guidance of the weapon can be carried out using computers on the manned aircraft and/or computers on the UAV.

Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.

Abstract: Systems and methods provide for edge protection and visual damage indication for a composite blade stringer. According to one aspect, an edge protection and visual indication system may be an edge treatment provided over an outer edge of a web of a composite blade stringer. The edge treatment may include a number of material layers encompassing the outer edge of the web and extending from a first surface of the web to a second surface of the web. The material layers may include a color contrasting layer and fiberglass layers. The material layers may alternatively include two overlapping, pre-cured angles.

Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.

Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.

Abstract: Packaged integrated circuits having inductors and methods to form inductors in packaged integrated circuits are disclosed. An example method comprises forming a substrate having a first trace and a contact, attaching an integrated circuit to the substrate over the first trace, and electrically coupling the first trace to the contact via an electrical conductor that extends over the integrated circuit to form the inductor in the packaged integrated circuit.

Abstract: A friction bolt assembly (1) comprises a friction bolt (2) with a pre-formed elongate column (3) of flexible, solid material retained within, and extending along a cavity (4) defined by the body (5) of the friction bolt (2). The body (5) of the friction bolt (2) is generally cylindrical and has a split (6) extending along its length.

Abstract: One embodiment of the invention includes a switching power supply system. The system includes a switch network comprising at least one switch configured to provide an output voltage based on switching activity thereof. The system also includes a switching controller configured to control the switch network to maintain the output voltage provided at an output based on a feedback signal associated with the output voltage. A converter pulse detector is configured to detect an output voltage overshoot condition based on the switching activity of the switch network corresponding to a transition in an output load to which the output voltage is provided.

Abstract: A method of assessing a multilayer strata (1) for rock bolt installation through a strata face (2) of said strata (1), comprises measuring potential differences between a first layer (3) of the strata (1) and each of one or more further layers (4, 5, 6, 7) of the strata (1).

Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.

Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.

Abstract: Packaged integrated circuits having inductors and methods to form inductors in packaged integrated circuits are disclosed. An example method comprises forming a substrate having a first trace and a contact, attaching an integrated circuit to the substrate over the first trace, and electrically coupling the first trace to the contact via an electrical conductor that extends over the integrated circuit to form the inductor in the packaged integrated circuit.

Abstract: Laminate structures and methods for forming same are disclosed. In one embodiment, a laminate structure includes a metal-polymer composite lamina. The metal-polymer composite lamina has a first face and a second face spaced apart, and extends to a terminal edge. The lamina includes a ply of fiber-reinforced polymer that extends between the first face and the second face and has an interior edge. The interior edge defines at least one cutout. A ply of metal foil extends between the first face and the second face substantially from the interior edge filling the at least one cutout.

Abstract: One embodiment of the invention includes a switching power supply system. The system includes a switch network comprising at least one switch configured to provide an output voltage based on switching activity thereof. The system also includes a switching controller configured to control the switch network to maintain the output voltage provided at an output based on a feedback signal associated with the output voltage. A converter pulse detector is configured to detect an output voltage overshoot condition based on the switching activity of the switch network corresponding to a transition in an output load to which the output voltage is provided.

Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.