Abstract: The range of energy transmissions or bursts (e.g., the range of high power microwave (HPM) directed energy weapons) may be increased using multiple sources (e.g., multiple HPM sources). For instance, according to techniques described herein, the individual sources may be fired at precise times such that the electromagnetic pulses are efficiently generated by each source and accurately add waveform peaks on the target. One or more aspects of the described techniques achieve sub-nanosecond timing accuracy by placing an HPM source, ultra-stable clock, and a laser pulse detector on each HPM weapon platform. For instance, the array may be triggered by firing a laser pulse at the target from one platform. By timing the firing of each HPM source based upon when the reflected laser pulse arrives at each platform as measured by the clock, the HPM pulses may arrive on target more accurately (e.g., more simultaneously).

Abstract: A folding trailing arm landing gear assembly having a main fitting configured to couple to a hinge positioned at a proximal end; a swing arm rotatably coupled at a proximal end to a distal end of the main fitting; a shock coupled at a distal end to a distal end of the swing arm; a bellcrank coupled at a distal end to a proximal end of the shock, and coupled at a proximal end to the main fitting; and a wheel coupled to the swing arm.

Abstract: A radome structure for a multilayered broadband radome structure is described. The radome structure may include a central core layer comprising a first dielectric constant, an interior intermediate core layer adjacent to an interior side of the central core layer, comprising a second dielectric constant less than the first dielectric constant, an exterior intermediate core layer adjacent to an exterior side of the central core layer, comprising a third dielectric constant less than the first dielectric constant, and an interior outside core layer adjacent to an interior side of the interior intermediate core layer, comprising a fourth dielectric constant less than the second dielectric constant. In some examples of the radome structure described above may further include an exterior outside core layer adjacent to an exterior side of the exterior intermediate core layer, comprising a low dielectric constant.

Abstract: This patent document relates to systems, structures, devices, and fabrication processes for ceramic matrix composites suitable for use in a nuclear reactor environment and other applications requiring materials that can withstand high temperatures and/or highly corrosive environments. In one exemplary aspect, a method of joining and sealing ceramic structures is disclosed. The method comprises forming a joint of a ceramic structure and an end plug using a sealing material, wherein the end plug has a hole that goes through a top surface and a bottom surface of the end plug; filling the ceramic structure with a desired gas composition through the hole; heating a material into a molten form using a heat source; and directing the material into the hole, wherein the material solidifies to seal the end plug.

Abstract: Fuel isolation systems, apparatuses and methods are described. In some embodiments, a system comprises a fuel tank, a fuel pump, an engine, a firewall, a fuel line from the fuel tank to the engine, a connector coupled inline with the fuel line on a cold side of the fuel line, a valve coupled to the connector, a fluid feed line coupled to a fluid source and to the valve. In the event of an engine fire condition, a control unit outputs signaling to turn off the fuel pump and operate the valve to introduce fluid from the fluid source into the fuel line. The introduced fluid provides a siphon break in the fuel line such that the only fuel that can pass the firewall is the remaining fuel in the fuel line downstream of the connector and the introduced fluid.

Abstract: Features for in-flight recovery of an unmanned aerial vehicle (UAV). A towline may be deployed by a host aircraft in-flight to recover an in-flight target UAV. The towline or portion thereof may be oriented nearly vertical. The towline may have a fitting thereon. A capture mechanism on the target UAV may have one or more deployable flaps that engage with the near vertical towline and fitting. The flaps may stow to secure the target aircraft to the towline and fitting. The host aircraft may then retract the towline to pull in the target UAV to the host aircraft using a hoist system having a winch. A latching system located in a pylon of the host aircraft, which may be under a wing, may have a towline connector that engages with and secures the target UAV. The host aircraft may have multiple hoist systems for deployment and/or recovery of multiple target UAV's.

Abstract: Disclosed are apparatuses, systems, methods, and devices for generating hydrogen pyrolysis of hydrocarbons (methane, diesel, JP8, etc.) in a reactor. The reactor includes multiple channels in parallel. A hydrocarbon flows in a channel and decomposes into hydrogen and carbon. Hydrogen gas flows out and some of the carbon will deposit on the channel wall. Once carbon deposition reaches a predetermined level, the hydrocarbon flow stops, and air or oxygen is caused to flow into the channels to oxidize carbon into carbon monoxide or carbon dioxide and supply heat to neighboring channels. Simultaneously, the hydrocarbon will flow into neighboring channels causing decomposition into hydrogen and carbon in the neighboring channels. When the carbon coating in the neighboring channels reaches a predetermined level, the gas flow is switched again to air or oxygen. In this way, each channel alternates between decomposing the hydrocarbon and oxidizing the deposited carbon.

Abstract: Some embodiments provide imaging polarimeter systems comprising: a polarization modulator system configured to modulate a polarization state of an incident beam at a repetition frequency, and outputting a polarized modulated beam; a polarizer positioned to produce an intensity modulated beam; and a detector system comprising: an optical sensor array; a digital read-out integrated circuit (DROIC); and a polarization state system; wherein the optical sensor array is optically aligned with at least a portion of the beam path such that the intensity modulated beam impinges on the sensor array; wherein the DROIC, for each pixel of the optical sensor array, is configured to separate, over time and within an integration frame rate, sets of photo-generated counts; and wherein the polarization state system is configured to identify a series of polarization states for each pixel based on the sets of photo-generated counts and according to the integration frame rate.

Abstract: In-flight recovery of an unmanned aerial vehicle (UAV). A towline may be deployed by a host aircraft in-flight in order to recover a target UAV that is also in-flight. A reel on the host aircraft may pay out the towline having a fitting thereon. A catch on the target UAV may engage with the fitting on the towline, and the reel may then retract the towline to thereby pull in the target UAV to the host aircraft. The target UAV may then securely attach with the host aircraft.

Abstract: A system for manufacturing a thermoplastic object may include a robotic arm configured to dispense thermoplastic material, a support apparatus, a computing device and an imaging system. The imaging system may scan thermoplastic material dispensed by the first robotic arm and create a three-dimensional scan model. The model may be compared to a computer model profile to determine if the dispensed material requires adjustment. If the dispensed material requires adjustment, the computing device may adjust the robotic arm or the support apparatus.

Abstract: Disclosed are apparatuses, systems, methods, and devices for generating high-pressure gas such as hydrogen and oxygen. In one aspect, an apparatus is disclosed. The apparatus includes a reactor which includes a pressure vessel containing a metal compound configured to react with a liquid to generate the high-pressure gas when the liquid is available in the vessel. The reactor includes an outlet configured to pass the generated high-pressure gas out of the vessel. The apparatus also includes a receiver configured to store the generated high-pressure gas generated in the vessel and passed to a receiver via the outlet or passed directly to fuel cell or vehicle tank.

Abstract: Features for in-flight recovery of an unmanned aerial vehicle (UAV). A towline may be deployed by a host aircraft in-flight to recover an in-flight target UAV. The towline or portion thereof may be oriented nearly vertical. The towline may have a fitting thereon. A capture mechanism on the target UAV may have one or more deployable flaps that engage with the near vertical towline and fitting. The flaps may stow to secure the target aircraft to the towline and fitting. The host aircraft may then retract the towline to pull in the target UAV to the host aircraft using a hoist system having a winch. A latching system located in a pylon of the host aircraft, which may be under a wing, may have a towline connector that engages with and secures the target UAV. The host aircraft may have multiple hoist systems for deployment and/or recovery of multiple target UAV's.

Abstract: A radome structure for a multilayered broadband radome structure is described. The radome structure may include a central core layer comprising a first dielectric constant, an interior intermediate core layer adjacent to an interior side of the central core layer, comprising a second dielectric constant less than the first dielectric constant, an exterior intermediate core layer adjacent to an exterior side of the central core layer, comprising a third dielectric constant less than the first dielectric constant, and an interior outside core layer adjacent to an interior side of the interior intermediate core layer, comprising a fourth dielectric constant less than the second dielectric constant. In some examples of the radome structure described above may further include an exterior outside core layer adjacent to an exterior side of the exterior intermediate core layer, comprising a low dielectric constant.

Abstract: Fuel isolation systems, apparatuses and methods are described. In some embodiments, a system comprises a fuel tank, a fuel pump, an engine, a firewall, a fuel line from the fuel tank to the engine, a connector coupled inline with the fuel line on a cold side of the fuel line, a valve coupled to the connector, an air feed line coupled to an air source and to the valve. In the event of an engine fire condition, a control unit outputs signaling to turn off the fuel pump and operate the valve to introduce air from the air source into the fuel line. The introduced air provides a siphon break in the fuel line such that the only fuel that can pass the firewall is the remaining fuel in the fuel line downstream of the connector and the introduced air.

Abstract: A folding trailing arm landing gear assembly having a main fitting configured to couple to a hinge positioned at a proximal end; a swing arm rotatably coupled at a proximal end to a distal end of the main fitting; a shock coupled at a distal end to a distal end of the swing arm; a bellcrank coupled at a distal end to a proximal end of the shock, and coupled at a proximal end to the main fitting; and a wheel coupled to the swing arm.

Abstract: A control system for an aero compression combustion drive assembly, the aero compression combustion drive assembly having an engine member, a transmission member and a propeller member, the control system including a sensor for sensing a pressure parameter in each of a plurality of compression chambers of the engine member, the sensor for providing the sensed pressure parameter to a control system device, the control system device having a plurality of control programs for effecting selected engine control and the control system device acting on the sensed pressure parameter to effect a control strategy in the engine member A control method is further included.

Abstract: A rotor for a rotating electric machine is described. Embodiments of the apparatus may include a rotor core comprising a plurality of slots, the rotor core comprising a circumference, a first winding comprising a first termination end exiting the rotor core at a first of the plurality of slots, a second winding comprising a second termination end exiting the rotor core at a second of the plurality of slots, wherein the second of the plurality of slots is 120 degrees around the circumference of the rotor core relative to the first of the plurality of slots, and a third winding comprising a third termination end exiting the rotor core at a third of the plurality of slots, wherein the third of the plurality of slots is 240 degrees around the circumference of the rotor core relative to the first of the plurality of slots.

Abstract: A ferritic aero diesel engine. The ferritic aero diesel engine includes an iron crankcase, a steel crankshaft and eight steel piston assemblies. The iron crankcase has a flat, horizontally opposed eight cylinder arrangement with a first set of cylinder walls defining a first set of cylinders in a first bank and a second set of cylinder walls defining a second set of cylinders in an opposed second bank. The steel crankshaft is rotatably mounted at least partially within the iron crankcase. Each of the steel piston assemblies of the plurality of steel piston assemblies is received within a respective cylinder of the iron crankcase and is coupled to the steel crankshaft. The first and second sets of cylinder walls have a minimum wall thickness of between approximately 4.8 and 5.2 mm.

Abstract: A battery system may include multiple battery cells grouped into modules. Each battery module may have a diffuser plate to direct the hot gases and molten material that are ejected during cell failure. The gas and material may be directed away from the nearest neighboring cells in the event of a single cell thermal runaway. Residual thermal energy is wicked away, absorbed or contained to keep heat away from the neighboring cells. These and other features may manage the blast energy and residual thermal energy of a single cell failure event. This may prevent a cascading failure of the larger battery system, thereby mitigating the risk of injury to personnel and property.

Abstract: A method and system for manufacturing potted electronic assemblies are described. Embodiments of the method and system may provide a potting compound having a first coefficient of thermal expansion different from a second coefficient of thermal expansion for a circuit board, provide a fiber reinforcement having a third coefficient of thermal expansion selected so that when the potting compound is combined with the fiber reinforcement the combined coefficient of thermal expansion is closer to the second coefficient of thermal expansion than the first coefficient of thermal expansion is to the second coefficient of thermal expansion, and apply the fiber reinforcement and the potting compound to the circuit board.